initial commit / add all books

author: priyanka 2015-06-24 15:03:17 +0530
committer: priyanka 2015-06-24 15:03:17 +0530
commit: b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b (patch)
tree: ab291cffc65280e58ac82470ba63fbcca7805165 /2223
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diff --git a/2223/CH11/EX11.1/Ex11_1.sav b/2223/CH11/EX11.1/Ex11_1.sav
new file mode 100755
index 000000000..cfdd690c9
--- /dev/null
+++ b/2223/CH11/EX11.1/Ex11_1.sav
diff --git a/2223/CH11/EX11.1/Ex11_1.sce b/2223/CH11/EX11.1/Ex11_1.sce
new file mode 100755
index 000000000..4fc5ae776
--- /dev/null
+++ b/2223/CH11/EX11.1/Ex11_1.sce
@@ -0,0 +1,56 @@
+// scilab Code Exa 11.1 Calculation on an axial compressor stage 
+
+Rm=0.5; // Degree of reaction
+funcprot(0);
+T1=300;  // in Kelvin
+p1=1; //  Initial Pressure in bar
+gamma=1.4;
+N=18e3; // rotor Speed in RPM
+d=36/100; // Mean Blade ring diameter in m
+h=6/100; // blade height at entry in m
+cx=180; // Axial velocity in m/s
+alpha_1=25;  //  air angle at rotor and stator exit
+wdf=0.88; // work-done factor
+m=70; //  in kg/s
+pr=2; // Pressure Ratio
+n_st=0.85; // Stage Efficiency 
+n_m=0.967; // Mechanical Efficiency 
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+u=%pi*d*N/60;
+n=(gamma-1)/gamma;
+
+// part(a) air angles at rotor and stator entry
+cy1=cx*tand(alpha_1);
+wy1=u-cy1;
+beta1=atand(wy1/cx);
+disp("degree",beta1,"air angles at rotor and stator entry are beta1=alpha2= ")
+phi=cx/u;
+
+// part(b) mass flow rate of the air
+ro1=(p1*1e5)/(R*T1);
+A1=%pi*d*h;
+m=ro1*cx*A1;
+disp("kg/s",m,"(b) mass flow rate of the air is")
+
+// part(c) Determining power required to drive the compressor
+beta2=alpha_1;
+w=wdf*u*cx*(tand(beta1)-tand(beta2))
+P=m*w/n_m;
+disp ("kW" ,P/1000,"(c)Power required to drive the compressor is")
+
+// part(d) Loading coefficient
+shi=w/(u^2);
+disp (shi,"(d)Loading coefficient is")
+
+// part(e) pressure ratio developed by the stage
+delTa=w/cp;
+delTs=n_st*delTa;
+pr=((1+(delTs/T1))^(1/n));
+disp(pr,"(e)pressure ratio developed by the stage is")
+
+// part(f) Mach number at the rotor entry
+w1=cx/(cosd(beta1));
+Mw1=w1/sqrt(gamma*R*T1);
+disp(Mw1,"(f)Mach number at the rotor entry is")
+
diff --git a/2223/CH11/EX11.2/Ex11_2.sav b/2223/CH11/EX11.2/Ex11_2.sav
new file mode 100755
index 000000000..3a01d3296
--- /dev/null
+++ b/2223/CH11/EX11.2/Ex11_2.sav
diff --git a/2223/CH11/EX11.2/Ex11_2.sce b/2223/CH11/EX11.2/Ex11_2.sce
new file mode 100755
index 000000000..86526cbb2
--- /dev/null
+++ b/2223/CH11/EX11.2/Ex11_2.sce
@@ -0,0 +1,50 @@
+// scilab Code Exa 11.2 Calculation on an axial compressor stage 
+
+T1=314;  // in Kelvin
+p1=768; //  Initial Pressure in mm Hg
+N=18e3; // rotor Speed in RPM
+d=50/100; // Mean Blade ring diameter in m
+u=100; // peripheral speed in m/s
+h=6/100; // blade height at entry in m
+beta1=51;
+beta2=9;
+alpha_1=7;  //  air angle at rotor and stator exit
+wdf=0.95; // work-done factor
+m=25; //  in kg/s
+n_st=0.88; // Stage Efficiency 
+n_m=0.92; // Mechanical Efficiency 
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+gamma=1.4;
+n=(gamma-1)/gamma;
+
+// part(a) air angle at stator entry
+cx=u/(tand(alpha_1)+tand(beta1));
+disp(cx,"cx=")
+alpha2=atand(tand(alpha_1)+tand(beta1)-tand(beta2))
+disp("degree",alpha2,"air angle at stator entry is alpha2= ")
+
+// part(b) blade height at entry and hub-tip diameter ratio
+ro1=(p1/750*1e5)/(R*T1);
+h1=m/(ro1*cx*%pi*d);
+disp("cm",h1*1e2,"(b)blade height at entry is")
+dh=d-h1;
+disp(dh,"dh=")
+dt=d+h1;
+disp(dt,"dt=")
+disp(dh/dt,"and hub-tip diameter ratio is")
+
+// part(c) stage Loading coefficient
+w=wdf*u*cx*(tand(beta1)-tand(beta2));
+shi=w/(u^2);
+disp (shi,"(d)Loading coefficient is")
+
+// part(d) stage pressure ratio
+delTa=w/cp;
+delTs=n_st*delTa;
+pr=((1+(delTs/T1))^(1/n));
+disp(pr,"(e)pressure ratio developed by the stage is")
+
+// part(e) Determining power required to drive the compressor
+P=m*w/n_m;
+disp ("kW" ,P/1000,"(e)Power required to drive the compressor is")
diff --git a/2223/CH11/EX11.3/Ex11_3.sav b/2223/CH11/EX11.3/Ex11_3.sav
new file mode 100755
index 000000000..5c227ad28
--- /dev/null
+++ b/2223/CH11/EX11.3/Ex11_3.sav
diff --git a/2223/CH11/EX11.3/Ex11_3.sce b/2223/CH11/EX11.3/Ex11_3.sce
new file mode 100755
index 000000000..38c69d840
--- /dev/null
+++ b/2223/CH11/EX11.3/Ex11_3.sce
@@ -0,0 +1,14 @@
+// scilab Code Exa 11.3 Calculation on an axial compressor stage
+
+// part(c) Verification of stage efficiency of exa 11.1
+beta1=54.82;
+alpha_1=25;
+beta2=alpha_1; 
+alpha_2=beta1;
+phi=0.53; // Flow coefficient
+YR=0.09; // loss coefficient for the blade rows
+n_st=1-((phi*YR*(secd(beta1)^2))/(tand(beta1)-tand(beta2)))
+disp("%",n_st*1e2,"stage efficiency n_st=")
+// part(d) Determining efficiencies of the rotor and Diffuser blade rows
+n_D=1-(YR/(1-((secd(alpha_1)^2)/(secd(alpha_2)^2))))
+disp ("%",n_D*100," Efficiency of the diffuser n_D=n_R=")
diff --git a/2223/CH11/EX11.4/Ex11_4.sav b/2223/CH11/EX11.4/Ex11_4.sav
new file mode 100755
index 000000000..9dc45b683
--- /dev/null
+++ b/2223/CH11/EX11.4/Ex11_4.sav
diff --git a/2223/CH11/EX11.4/Ex11_4.sce b/2223/CH11/EX11.4/Ex11_4.sce
new file mode 100755
index 000000000..e4d18ece7
--- /dev/null
+++ b/2223/CH11/EX11.4/Ex11_4.sce
@@ -0,0 +1,78 @@
+// scilab Code Exa 11.4 Calculation on hub,mean and tip sections 
+
+dm=50/100; // Mean Blade ring diameter in m
+rm=dm/2;
+dh=0.3098354; // from results of exa 11.2
+dt=0.6901646;
+um=100; // peripheral speed in m/s
+beta_1m=51;
+beta_2m=9;
+alpha_1m=7;  //  air angle at rotor and stator exit
+alpha_2m=50.177922;
+omega=um/rm;
+rh=dh/2;
+rt=dt/2;
+uh=omega*rh;
+ut=omega*rt;
+
+// part(a) rotor blade air angles
+cx=73.654965;
+c_theta1m=cx*tand(alpha_1m);
+C1=rm*c_theta1m;
+c_theta1h=C1/rh;
+c_theta1t=C1/rt;
+c_theta2m=cx*tand(alpha_2m);
+C2=rm*c_theta2m;
+c_theta2h=C2/rh;
+c_theta2t=C2/rt;
+disp("(a) the rotor blade air angles are")
+// for hub section
+alpha1h=atand(C1/(rh*cx));
+alpha2h=atand(C2/(rh*cx));
+disp("for hub section")
+disp("degree",alpha1h,"alpha1h=")
+disp("degree",alpha2h,"alpha2h=")
+beta1h=atand((uh/cx)-tand(alpha1h));
+beta2h=atand((uh/cx)-tand(alpha2h));
+disp("degree",beta1h,"beta1h=")
+disp("degree",beta2h,"beta2h=")
+
+// for tip section
+alpha1t=atand(C1/(rt*cx));
+alpha2t=atand(C2/(rt*cx));
+disp("for tip section")
+disp("degree",alpha1t,"alpha1t= ")
+disp("degree",alpha2t,"alpha2t= ")
+beta1t=atand((ut/cx)-tand(alpha1t));
+beta2t=atand((ut/cx)-tand(alpha2t));
+disp("degree",beta1t,"beta1t= ")
+disp("degree",beta2t,"beta2t= ")
+
+// part(b)Flow coefficients
+disp("(b)Flow coefficients are")
+phi_h=cx/uh;
+disp(phi_h,"phi_h=")
+phi_m=cx/um;
+disp(phi_m,"phi_m=")
+phi_t=cx/ut;
+disp(phi_t,"phi_t=")
+// part(c) degrees of reaction
+disp("(c)Degrees of reaction are")
+Rh=cx*(tand(beta1h)+tand(beta2h))*100/(2*uh);
+disp("%",Rh,"Rh=")
+Rm=cx*(tand(beta_1m)+tand(beta_2m))*100/(2*um);
+disp("%",Rm,"Rm=")
+Rt=cx*(tand(beta1t)+tand(beta2t))*100/(2*ut);
+disp("%",Rt,"Rt=")
+
+// part(d) specific work
+w=omega*(C2-C1);
+disp("kJ/kg",w*1e-3,"(d)specific work is")
+// part(e) the loading coefficients
+disp("(e)the loading coefficients are")
+shi_h=w/(uh^2);
+disp(shi_h,"shi_h=")
+shi_m=w/(um^2);
+disp(shi_m,"shi_m=")
+shi_t=w/(ut^2);
+disp(shi_t,"shi_t=")
diff --git a/2223/CH11/EX11.5/Ex11_5.sav b/2223/CH11/EX11.5/Ex11_5.sav
new file mode 100755
index 000000000..122fe9357
--- /dev/null
+++ b/2223/CH11/EX11.5/Ex11_5.sav
diff --git a/2223/CH11/EX11.5/Ex11_5.sce b/2223/CH11/EX11.5/Ex11_5.sce
new file mode 100755
index 000000000..19b8ab9e8
--- /dev/null
+++ b/2223/CH11/EX11.5/Ex11_5.sce
@@ -0,0 +1,75 @@
+// scilab Code Exa 11.5 Forced Vortex axial compressor stage 
+
+dm=50/100; // Mean Blade ring diameter in m
+rm=dm/2;
+dh=0.3098354; // from results of exa 11.2
+dt=0.6901646;
+um=100; // peripheral speed in m/s
+beta_1m=51;
+beta_2m=9;
+alpha_1m=7;  //  air angle at rotor and stator exit
+alpha_2m=50.177922;
+omega=um/rm;
+rh=dh/2;
+rt=dt/2;
+uh=omega*rh;
+ut=omega*rt;
+// part(a) rotor blade air angles
+cx=73.654965;
+c_theta1m=cx*tand(alpha_1m);
+C1=c_theta1m/rm;
+c_theta1h=C1*rh;
+c_theta1t=C1*rt;
+K1=cx^2+(2*(C1^2)*(rm^2));
+cx1h=sqrt(K1-(2*(C1^2)*(rh^2)));
+cx1t=sqrt(K1-(2*(C1^2)*(rt^2)));
+c_theta2m=cx*tand(alpha_2m);
+C2=c_theta2m/rm;
+c_theta2h=C2*rh;
+c_theta2t=C2*rt;
+K2=cx^2-(2*(C2-C1)*omega*(rm^2))+(2*(C2^2)*(rm^2));
+cx2h=sqrt(K2+(2*(C2-C1)*omega*(rh^2))-(2*(C2^2)*(rh^2)));
+cx2t=sqrt(K2+(2*(C2-C1)*omega*(rt^2))-(2*(C2^2)*(rt^2)));
+disp("(a) the rotor blade air angles are")
+// for hub section
+alpha1h=atand(C1*rh/cx1h);
+alpha2h=atand(C2*rh/cx2h);
+disp("for hub section")
+beta1h=atand((uh/cx1h)-tand(alpha1h));
+beta2h=atand((uh/cx2h)-tand(alpha2h));
+disp("degree",beta1h,"beta1h=")
+disp("degree",beta2h,"beta2h=")
+
+// for tip section
+alpha1t=atand(C1*rt/cx1t);
+alpha2t=atand(C2*rt/cx2t);
+disp("for tip section")
+beta1t=atand((ut/cx1t)-tand(alpha1t));
+beta2t=atand((ut/cx2t)-tand(alpha2t));
+disp("degree",beta1t,"beta1t= ")
+disp("degree",beta2t,"beta2t= ")
+
+// part(b) specific work
+wh=omega*(C2-C1)*(rh^2);
+wm=omega*(C2-C1)*(rm^2);
+wt=omega*(C2-C1)*(rt^2);
+disp("kJ/kg",wh*1e-3,"(b)specific work at hub is")
+disp("kJ/kg",wm*1e-3,"specific work at mean section is")
+disp("kJ/kg",wt*1e-3,"specific work at tip is")
+// part(c) the loading coefficients
+disp("(c)the loading coefficients are")
+shi_h=wh/(uh^2);
+disp(shi_h,"shi_h=")
+shi_m=wm/(um^2);
+disp(shi_m,"shi_m=")
+shi_t=wt/(ut^2);
+disp(shi_t,"shi_t=")
+
+// part(c) degrees of reaction
+disp("(d)Degrees of reaction are")
+Rh=((cx1h^2)*(secd(beta1h)^2)-(cx2h^2)*(secd(beta2h)^2))*100/(2*wh);
+Rm=((cx^2)*(secd(beta_1m)^2)-(cx^2)*(secd(beta_2m)^2))*100/(2*wm);
+Rt=((cx1t^2)*(secd(beta1t)^2)-(cx2t^2)*(secd(beta2t)^2))*100/(2*wt);
+disp("%",Rh,"Rh=")
+disp("%",Rm,"Rm=")
+disp("%",Rt,"Rt=")
diff --git a/2223/CH11/EX11.6/Ex11_6.sav b/2223/CH11/EX11.6/Ex11_6.sav
new file mode 100755
index 000000000..7e94b577d
--- /dev/null
+++ b/2223/CH11/EX11.6/Ex11_6.sav
diff --git a/2223/CH11/EX11.6/Ex11_6.sce b/2223/CH11/EX11.6/Ex11_6.sce
new file mode 100755
index 000000000..92a67d559
--- /dev/null
+++ b/2223/CH11/EX11.6/Ex11_6.sce
@@ -0,0 +1,75 @@
+// scilab Code Exa 11.6 General Swirl Distribution axial compressor 
+
+Rm=0.5; // Degree of reaction
+dm=36/100; // Mean Blade ring diameter in m
+rm=dm/2;
+N=18e3; // rotor Speed in RPM
+h=6/100; // blade height at entry in m
+dh=dm-h;
+dt=dm+h;
+cx=180; // Axial velocity in m/s
+alpha_1m=25;  //  air angle at rotor and stator exit
+alpha_2m=54.820124;  
+um=%pi*dm*N/60;
+omega=um/rm;
+rh=dh/2;
+rt=dt/2;
+uh=omega*rh;
+ut=omega*rt;
+
+// part(a) rotor blade air angles
+c_theta1m=cx*tand(alpha_1m);
+c_theta2m=cx*tand(alpha_2m);
+a=0.5*(c_theta1m+c_theta2m)
+b=rm*(c_theta2m-c_theta1m)*0.5;
+c_theta1h=a-(b/rh);
+c_theta1t=a-(b/rt);
+K1=cx^2+(2*(a^2)*((b/(a*rm))+log(rm)));
+cx1h=sqrt(K1-(2*(a^2)*((b/(a*rh))+log(rh))));
+cx1t=sqrt(K1-(2*(a^2)*((b/(a*rt))+log(rt))));
+
+c_theta2h=a+(b/rh);
+c_theta2t=a+(b/rt);
+K2=cx^2+(2*(a^2)*(log(rm)-(b/(a*rm))));
+cx2h=sqrt(K2-(2*(a^2)*(log(rh)-(b/(a*rh)))));
+cx2t=sqrt(K2-(2*(a^2)*(log(rt)-(b/(a*rt)))));
+disp("(a) the rotor blade air angles are")
+// for hub section
+alpha1h=atand(c_theta1h/cx1h);
+alpha2h=atand(c_theta2h/cx2h);
+disp("for hub section")
+beta1h=atand((uh/cx1h)-tand(alpha1h));
+beta2h=atand((uh/cx2h)-tand(alpha2h));
+disp("degree",beta1h,"beta1h=")
+disp("degree",beta2h,"beta2h=")
+
+// for tip section
+alpha1t=atand(c_theta1t/cx1t);
+alpha2t=atand(c_theta2t/cx2t);
+disp("for tip section")
+beta1t=atand((ut/cx1t)-tand(alpha1t));
+beta2t=atand((ut/cx2t)-tand(alpha2t));
+disp("degree",beta1t,"beta1t= ")
+disp("degree",beta2t,"beta2t= ")
+
+// part(b) specific work
+w=2*omega*b;
+disp("kJ/kg",w*1e-3,"(b)specific work is")
+
+// part(c) the loading coefficients
+disp("(c)the loading coefficients are")
+shi_h=w/(uh^2);
+disp(shi_h,"shi_h=")
+shi_m=w/(um^2);
+disp(shi_m,"shi_m=")
+shi_t=w/(ut^2);
+disp(shi_t,"shi_t=")
+
+// part(c) degrees of reaction
+disp("(d)Degrees of reaction are")
+Rh=((cx1h^2)*(secd(beta1h)^2)-(cx2h^2)*(secd(beta2h)^2))*100/(2*w);
+Rt=((cx1t^2)*(secd(beta1t)^2)-(cx2t^2)*(secd(beta2t)^2))*100/(2*w);
+disp("%",Rh,"Rh=")
+disp("%",Rm*100,"Rm=")
+disp("%",Rt,"Rt=")
+disp("Comment: book contains wrong calculation for Rt value")
diff --git a/2223/CH11/EX11.7/Ex11_7.sav b/2223/CH11/EX11.7/Ex11_7.sav
new file mode 100755
index 000000000..e1c5ecb05
--- /dev/null
+++ b/2223/CH11/EX11.7/Ex11_7.sav
diff --git a/2223/CH11/EX11.7/Ex11_7.sce b/2223/CH11/EX11.7/Ex11_7.sce
new file mode 100755
index 000000000..1c1c510eb
--- /dev/null
+++ b/2223/CH11/EX11.7/Ex11_7.sce
@@ -0,0 +1,16 @@
+// scilab Code Exa 11.7 flow and loading coefficients 
+u=339.29; // in m/s
+cx=180; // Axial velocity in m/s
+alpha_1m=25;  //  air angle at rotor and stator exit
+phi(1)=0.2;
+phi(2)=0.4;
+phi(3)=cx/u;
+phi(4)=0.6;
+phi(5)=0.8;
+n=5;
+for i=1:n
+    shi(i)=1-phi(i)*(2*tand(alpha_1m));
+    disp(phi(i),"when flow coefficient phi=")
+    disp(shi(i),"then loading coefficient shi=")
+end
+
diff --git a/2223/CH12/EX12.1/Ex12_1.sav b/2223/CH12/EX12.1/Ex12_1.sav
new file mode 100755
index 000000000..c7cb3051d
--- /dev/null
+++ b/2223/CH12/EX12.1/Ex12_1.sav
diff --git a/2223/CH12/EX12.1/Ex12_1.sce b/2223/CH12/EX12.1/Ex12_1.sce
new file mode 100755
index 000000000..a5fdb5228
--- /dev/null
+++ b/2223/CH12/EX12.1/Ex12_1.sce
@@ -0,0 +1,41 @@
+// scilab Code Exa 12.1 Calculation on a centrifugal compressor stage 
+T01=335;  // in Kelvin
+funcprot(0);
+p01=1.02; //  Initial Pressure in bar
+dh=0.10; // hub diameter in m
+dt=0.25; // tip diameter in m
+m=5; //  in kg/s
+gamma=1.4;
+N=7.2e3; // rotor Speed in RPM
+d1=0.5*(dt+dh); // Mean Blade ring diameter
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+A=%pi*((dt^2)-(dh^2))/4;
+R=287;
+// I trial
+ro1=(p01*1e5)/(R*T01);
+cx0=m/(ro1*A);
+T0=T01-((cx0^2)/(2*cp));
+n=(gamma-1)/gamma;
+p1=p01*((T0/T01)^(1/n));
+ro=(p1*1e5)/(R*T0);
+cx=m/(ro*A);
+// II Trial
+cx2=123;
+T1=T01-((cx2^2)/(2*cp));
+p2=p01*((T1/T01)^(1/n));
+ro2=(p2*1e5)/(R*T1);
+cx1=m/(ro2*A);
+u1=%pi*d1*N/60;
+beta1=atand(cx1/u1);
+disp("degree",beta1,"air angle at inducer blade entry beta1=")
+w1=cx1/(sind(beta1));
+a1=sqrt(gamma*R*T1);
+Mw1=w1/a1;
+disp(Mw1,"the Relative Mach number at inducer blade entry Mw1=")
+alpha1=atand(cx1/u1);
+disp("degree",alpha1,"air angle at IGVs exit alpha1=")
+c1=cx1/(sind(alpha1));
+T1_new=T01-((c1^2)/(2*cp));
+a1_new=sqrt(gamma*R*T1_new);
+Mw1_new=cx1/a1_new;
+disp(Mw1_new,"the new value of Relative Mach number Mw1_new=")
diff --git a/2223/CH12/EX12.2/Ex12_2.sav b/2223/CH12/EX12.2/Ex12_2.sav
new file mode 100755
index 000000000..0c221e587
--- /dev/null
+++ b/2223/CH12/EX12.2/Ex12_2.sav
diff --git a/2223/CH12/EX12.2/Ex12_2.sce b/2223/CH12/EX12.2/Ex12_2.sce
new file mode 100755
index 000000000..e4b3203a2
--- /dev/null
+++ b/2223/CH12/EX12.2/Ex12_2.sce
@@ -0,0 +1,16 @@
+// scilab Code Exa 12.2 Calculation on a centrifugal air compressor 
+T01=288;  // in Kelvin
+p01=1.02; //  Initial Pressure in bar
+dh=0.10; // hub diameter in m
+dt=0.25; // tip diameter in m
+m=5; //  in kg/s
+gamma=1.4;
+n=(gamma-1)/gamma;
+N=7.2e3; // rotor Speed in RPM
+d2=0.45; // Impeller diameter in m
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+u2=%pi*d2*N/60;
+pr0=((1+(u2^2/(cp*T01)))^(1/n));
+disp(pr0,"pressure ratio developed pr0=")
+w=u2^2;
+disp("kW/(kg/s)",w*1e-3,"Power required to drive the compressor P=")
diff --git a/2223/CH12/EX12.3/Ex12_3.sav b/2223/CH12/EX12.3/Ex12_3.sav
new file mode 100755
index 000000000..174bf5a45
--- /dev/null
+++ b/2223/CH12/EX12.3/Ex12_3.sav
diff --git a/2223/CH12/EX12.3/Ex12_3.sce b/2223/CH12/EX12.3/Ex12_3.sce
new file mode 100755
index 000000000..35583d9f7
--- /dev/null
+++ b/2223/CH12/EX12.3/Ex12_3.sce
@@ -0,0 +1,75 @@
+// scilab Code Exa 12.3 Calculation on a centrifugal compressor stage 
+
+funcprot(0)
+T01=306;  // Entry Temperature in Kelvin
+p01=1.05; //  Entry Pressure in bar
+dh=0.12; // hub diameter in m
+dt=0.24; // tip diameter in m
+m=8; //  in kg/s
+mu=0.92; // slip factor
+n_st=0.77; // stage efficiency
+gamma=1.4;
+N=17e3; // rotor Speed in RPM
+d_it=0.48; // Impeller tip diameter in m
+d1=0.5*(dt+dh); // Mean Blade ring diameter
+rm=d1/2;
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+A=%pi*((dt^2)-(dh^2))/4;
+R=287;
+n=86; // number of iterations
+ro01=(p01*1e5)/(R*T01);
+cx(1)=m/(ro01*A);
+for i=1:n
+    T1=T01-((cx(i)^2)/(2*cp));
+    p1=p01*((T1/T01)^(1/((gamma-1)/gamma)));
+ro1=(p1*1e5)/(R*T1);
+cx(i+1)=m/(ro1*A);
+if cx(i+1)==cx(i) then
+    disp("m/s",cx(i+1),"cx=")
+    disp(T1,"T1")
+disp(p1,"p1")
+disp(ro1,"ro1")
+end 
+end
+cx1=cx(i+1);
+u1m=%pi*d1*N/60;
+omega=u1m/rm;
+rh=dh/2;
+rt=dt/2;
+uh=omega*rh;
+ut=omega*rt;
+u2=d_it*u1m/d1;
+beta1h=atand(cx1/uh);
+beta1m=atand(cx1/u1m);
+beta1t=atand(cx1/ut);
+disp("(a) Without IGVs")
+disp("degree",beta1h,"air angle at hub section beta1h=")
+disp("degree",beta1m,"air angle at mean section beta1m=")
+disp("degree",beta1t,"air angle at tip section beta1t=")
+w1t=cx1/(sind(beta1t));
+a1=sqrt(gamma*R*T1);
+M1t=w1t/a1;
+disp(M1t,"the maximum Mach number at inducer blade entry M1t=")
+pr0=((1+(mu*n_st*(u2^2)/(cp*T01)))^(1/((gamma-1)/gamma)));
+disp(pr0,"total pressure ratio developed is")
+P=m*mu*(u2^2);
+disp ("kW",P/1000,"Power required to drive the compressor without IGVs is")
+
+// part(b) with IGVs
+alpha1h=beta1h;
+alpha1m=beta1m;
+alpha1t=beta1t;
+disp("(b)With IGVs")
+disp("degree",alpha1h,"air angle at hub section alpha1h=")
+disp("degree",alpha1m,"air angle at mean section alpha1m=")
+disp("degree",alpha1t,"air angle at tip section alpha1t=")
+c1t=cx1/(sind(alpha1t));
+T1t=T01-((c1t^2)/(2*cp));
+a1t=sqrt(gamma*R*T1t);
+Mw1t=cx1/a1t;
+disp(Mw1t,"the maximum Mach number at inducer blade entry Mw1t=")
+pr0_w=((1+(n_st*(mu*(u2^2)-(u1m^2))/(cp*T01)))^(1/((gamma-1)/gamma)));
+disp(pr0_w,"total pressure ratio developed is")
+P_w=m*(mu*(u2^2)-(u1m^2));
+disp ("kW",P_w/1000,"Power required to drive the compressor is")
+disp("Comment: here the solution is found out using programming, so this gives slightly small variation from tha answers given in hte book, but answers from the present solution are exact.")
diff --git a/2223/CH12/EX12.4/Ex12_4.sav b/2223/CH12/EX12.4/Ex12_4.sav
new file mode 100755
index 000000000..799be69eb
--- /dev/null
+++ b/2223/CH12/EX12.4/Ex12_4.sav
diff --git a/2223/CH12/EX12.4/Ex12_4.sce b/2223/CH12/EX12.4/Ex12_4.sce
new file mode 100755
index 000000000..f87ca5334
--- /dev/null
+++ b/2223/CH12/EX12.4/Ex12_4.sce
@@ -0,0 +1,15 @@
+// scilab Code Exa 12.4.b Radially tipped blade impeller
+phi2=0.268; // Flow coefficient
+T01=293;  // in Kelvin
+p01=1; //  Initial Pressure in bar
+dr=2.667; // diameter ratio(d2/d1)
+gamma=1.4;
+R=287;
+N=8e3; // rotor Speed in RPM
+d1=0.18; // Mean diameter at the impeller entry in m
+u1=%pi*d1*N/60;
+a1=sqrt(gamma*R*T01);
+Mb1=u1/a1;
+disp(Mb1,"the Mach number at inducer blade entry Mb1=")
+M2=sqrt(((dr^2)*(Mb1^2)*(1+(phi2^2)))/(1+(0.5*(gamma-1)*(dr^2)*(Mb1^2)*(1-(phi2^2)))));
+disp(M2,"the flow Mach number at impeller exit M2=")
diff --git a/2223/CH12/EX12.5/Ex12_5.sav b/2223/CH12/EX12.5/Ex12_5.sav
new file mode 100755
index 000000000..5eb2e024c
--- /dev/null
+++ b/2223/CH12/EX12.5/Ex12_5.sav
diff --git a/2223/CH12/EX12.5/Ex12_5.sce b/2223/CH12/EX12.5/Ex12_5.sce
new file mode 100755
index 000000000..5badb2eb2
--- /dev/null
+++ b/2223/CH12/EX12.5/Ex12_5.sce
@@ -0,0 +1,36 @@
+// scilab Code Exa 12.5 Radially tipped blade impeller
+// part(a) free vortex flow
+r3=0.25; // volute base circle radius in m
+c_theta3=177.5; // tangential velocity component of air in m/s
+K=r3*c_theta3;
+b=0.12; // width in m
+Q=5.4; // discharge in m3/s
+n=8;
+disp("part(a)")
+theta(1)=%pi/4;
+theta(2)=%pi/2;
+theta(3)=3*%pi/4;
+theta(4)=%pi;
+theta(5)=5*%pi/4;
+theta(6)=3*%pi/2;
+theta(7)=7*%pi/4;
+theta(8)=2*%pi;
+disp("the volute radii at eight angular positions are given below:")
+for i=1:n
+    r4(i)=r3*exp(theta(i)*Q/(2*%pi*K*b))
+    disp("radian",theta(i),"at theta=")
+    disp("cm",r4(i)*100,"r4=")
+end
+L=r4(8)-r3;
+disp(L/(2*r3),"(a)throat-to-diameter ratio (L/d3)=")
+
+// part(b) constant mean velocity of 145 m/s
+cm=145; // constant mean velocity in m/s
+disp("part(b)")
+for i=1:n
+    r4b(i)=r3+(Q/(cm*b)*(theta(i)/(2*%pi)));
+    disp("radian",theta(i),"at theta=")
+    disp("cm",r4b(i)*100,"r4=")
+end
+L_b=r4b(8)-r3;
+disp(L_b/(2*r3),"(b)throat-to-diameter ratio (L/d3)=")
diff --git a/2223/CH13/EX13.1/Ex13_1.sav b/2223/CH13/EX13.1/Ex13_1.sav
new file mode 100755
index 000000000..928f13b99
--- /dev/null
+++ b/2223/CH13/EX13.1/Ex13_1.sav
diff --git a/2223/CH13/EX13.1/Ex13_1.sce b/2223/CH13/EX13.1/Ex13_1.sce
new file mode 100755
index 000000000..3a9592f71
--- /dev/null
+++ b/2223/CH13/EX13.1/Ex13_1.sce
@@ -0,0 +1,56 @@
+// scilab Code Exa 13.1 ninety degree IFR turbine
+t=650; // in degree C
+T01=t+273; // in Kelvin
+p3=1; //  Exit Pressure in bar
+gamma=1.4;
+sigma=0.66; // blade-to-isentropic speed ratio
+N=16e3; // rotor Speed in RPM
+b2=5/100; // blade height at entry in m
+alpha_2=20;  //  air angle at nozzle exit
+d_r=0.45; // rotor diameter ratio(d3/d2)
+p01_3=3.5; // total-to-static Pressure Ratio(p01/p3) 
+n_N=0.95; // Nozzle Efficiency 
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+n=(gamma-1)/gamma;
+
+// part(a) the rotor diameter
+c_0=sqrt(2*cp*T01*(1-(p01_3^(-n))))
+u_2=sigma*c_0;
+d2=60*u_2/(%pi*N);
+disp("cm",d2*1e2,"(a)the rotor diameter is")
+
+// part(b) air angle at rotor blade exit
+d3=d2*d_r;
+c_r2=u_2*tand(alpha_2);
+u3=%pi*d3*N/60;
+beta3=atand(c_r2/u3);
+disp("degree",beta3,"(b) air angle at rotor blade exit beta3=")
+
+// part(c) mass flow rate
+T03=T01-((u_2^2)/cp);
+T3=T03-((c_r2^2)/(2*cp));
+T2=T3+((0.5*(u_2^2))/cp);
+c2=u_2/(cosd(alpha_2));
+p01_2=(1-(((0.5*(c2^2))/(cp*n_N))/T01))^(-1/n);
+p01=p3*p01_3;
+p2=p01/p01_2;
+ro2=(p2*1e5)/(R*T2);
+m=ro2*c_r2*%pi*d2*b2;
+disp("kg/s",m,"(c) mass flow rate is")
+
+// part(d) hub and tip diameters at the rotor exit
+ro3=(p3*1e5)/(R*T3);
+b3=m/(ro3*c_r2*%pi*d3);
+dh=d3-b3;
+disp("cm",dh*1e2,"(d)hub diameter at the rotor exit is")
+dt=d3+b3;
+disp("cm",dt*1e2,"(d)tip diameter at the rotor exit is")
+
+// part(e) Determining the power developed
+P=m*(u_2^2);
+disp ("kW",P/1000,"(e)Power developed is")
+
+// part(f) the total-to-static Efficiency of the stage
+n_ts=(u_2^2)/(cp*T01*(1-((p3/p01)^n)));
+disp("%",n_ts*1e2,"(f)the total-to-static Efficiency of the stage is")
diff --git a/2223/CH13/EX13.2/Ex13_2.sav b/2223/CH13/EX13.2/Ex13_2.sav
new file mode 100755
index 000000000..dfec0b623
--- /dev/null
+++ b/2223/CH13/EX13.2/Ex13_2.sav
diff --git a/2223/CH13/EX13.2/Ex13_2.sce b/2223/CH13/EX13.2/Ex13_2.sce
new file mode 100755
index 000000000..980d10dae
--- /dev/null
+++ b/2223/CH13/EX13.2/Ex13_2.sce
@@ -0,0 +1,53 @@
+// scilab Code Exa 13.2 Mach Number and loss coefficient
+t=650; // in degree C
+T01=t+273; // in Kelvin
+p3=1; //  Exit Pressure in bar
+gamma=1.4;
+sigma=0.66; // blade-to-isentropic speed ratio
+N=16e3; // rotor Speed in RPM
+b2=5/100; // blade height at entry in m
+alpha_2=20;  //  air angle at nozzle exit
+d_r=0.45; // rotor diameter ratio(d3/d2)
+p01_3=3.5; // total-to-static Pressure Ratio(p01/p3) 
+n_N=0.95; // Nozzle Efficiency 
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+n=(gamma-1)/gamma;
+c_0=sqrt(2*cp*T01*(1-(p01_3^(-n))))
+u_2=sigma*c_0;
+Mb0=u_2/sqrt(gamma*R*T01);
+
+// part(a) Mach number at nozzle exit
+M2=Mb0/(cosd(alpha_2)*sqrt(1-(0.5*(gamma-1)*(Mb0^2)*(secd(alpha_2)^2))));
+disp(M2,"(a)the flow Mach number at nozzle exit M2=")
+
+// part(b)rotor exit Relative Mach number
+d2=60*u_2/(%pi*N);
+d3=d2*d_r;
+c_r2=u_2*tand(alpha_2);
+u3=%pi*d3*N/60;
+beta3=atand(c_r2/u3);
+w3=u3/(cosd(beta3));
+T03=T01-((u_2^2)/cp);
+T3=T03-((c_r2^2)/(2*cp));
+a3=sqrt(gamma*R*T3);
+M3_rel=w3/a3;
+disp(M3_rel,"(b)the Relative Mach number at rotor exit is")
+
+// part(c) Nozzle enthalpy loss coefficient
+T2=T3+((0.5*(u_2^2))/cp);
+c2=u_2/(cosd(alpha_2));
+T2s=T01-((0.5*(c2^2))/(cp*n_N));
+c2=u_2/(cosd(alpha_2));
+zeeta_N=cp*(T2-T2s)/(0.5*(c2^2));
+disp(zeeta_N,"(c)the Nozzle enthalpy loss coefficient is")
+
+// part(d)rotor enthalpy loss coefficient
+
+p01_2=(1-(((0.5*(c2^2))/(cp*n_N))/T01))^(-1/n);
+p01=p3*p01_3;
+p2=p01/p01_2;
+T3s=T2/((p2/p3)^n);
+zeeta_R=cp*(T3-T3s)/(0.5*(w3^2));
+disp(zeeta_R,"(d)the rotor enthalpy loss coefficient is")
+disp("comment: Nozzle enthalpy loss coefficient value is not correctly calculated in the textbook. the above value is correct.")
diff --git a/2223/CH13/EX13.3/Ex13_3.sav b/2223/CH13/EX13.3/Ex13_3.sav
new file mode 100755
index 000000000..fe23c6ec6
--- /dev/null
+++ b/2223/CH13/EX13.3/Ex13_3.sav
diff --git a/2223/CH13/EX13.3/Ex13_3.sce b/2223/CH13/EX13.3/Ex13_3.sce
new file mode 100755
index 000000000..5e67a2dc4
--- /dev/null
+++ b/2223/CH13/EX13.3/Ex13_3.sce
@@ -0,0 +1,28 @@
+// scilab Code Exa 13.3 IFR turbine with Cantilever Blades
+phi=0.4; // flow coefficient
+funcprot(0);
+P=100; // Power developed in kW
+n_tt=0.9; // total-to-total Efficiency
+N=12e3; // rotor Speed in RPM
+m=1; // in kg/s
+T01=400;  // in Kelvin
+gamma=1.4;
+d_r=0.8; // rotor diameter ratio(d3/d2)
+u2=sqrt(P*1000/(2*m));
+d2=60*u2/(%pi*N);
+disp("cm",d2*1e2,"the rotor diameter at entry is")
+d3=d2*d_r;
+disp("cm",d3*1e2,"the rotor diameter at exit is")
+beta2=atand(phi);
+disp("degree",beta2,"air angle at rotor entry is beta2=")
+d3=d2*d_r;
+u3=%pi*d3*N/60;
+c_r2=u2*phi;
+beta3=atand(c_r2/u3);
+disp("degree",beta3,"air angle at rotor exit is beta3=")
+cp=1005;
+n=(gamma-1)/gamma;
+alpha_2=atand(c_r2/(2*u2));
+disp("degree",alpha_2,"air angle at nozzle exit is alpha_2=")
+p01_03=(1-((2*(u2^2))/(n_tt*cp*T01)))^(-1/n);
+disp(p01_03,"stagnation pressure ratio across the stage is")
diff --git a/2223/CH14/EX14.1/Ex14_1.sav b/2223/CH14/EX14.1/Ex14_1.sav
new file mode 100755
index 000000000..3db4b7bd1
--- /dev/null
+++ b/2223/CH14/EX14.1/Ex14_1.sav
diff --git a/2223/CH14/EX14.1/Ex14_1.sce b/2223/CH14/EX14.1/Ex14_1.sce
new file mode 100755
index 000000000..f3fd71972
--- /dev/null
+++ b/2223/CH14/EX14.1/Ex14_1.sce
@@ -0,0 +1,30 @@
+// scilab Code Exa 14.1 Axial fan stage 960 rpm
+beta3=10; // rotor blade air angle at exit in degree
+dh=0.3; // hub diameter in m
+dt=0.6; // tip diameter in m
+N=960; // rotor Speed in RPM
+P=1; // Power required in kW
+phi=0.245; // flow coefficient
+T1=316;  // in Kelvin
+p1=1.02; //Initial Pressure in bar
+R=287;
+A=%pi*((dt^2)-(dh^2))/4;
+d=0.5*(dt+dh);
+u=%pi*d*N/60;
+cx=phi*u;
+Q=cx*A;
+ro=(p1*1e5)/(R*T1);
+delp0_st=ro*(u^2)*(1-(phi*(tand(beta3))));
+disp("mm W.G.",delp0_st/9.81,"stage pressure rise is")
+IP=Q*delp0_st/1000; // ideal power required to drive the fan in kW
+n_o=IP/P;
+disp("%",n_o*1e2,"the overall Efficiency of the fan is") 
+beta2=atand(u/cx);
+disp("degree",beta2,"the blade air angle at the entry beta2=")
+delp_st=0.5*ro*(u^2)*(1-(phi^2*(tand(beta3)^2)));
+DOR=delp_st/delp0_st;
+disp("%",DOR*1e2,"the degree of reaction is") 
+omega=2*%pi*N/60;
+gH=delp0_st/ro;
+NS=omega*sqrt(Q)/(gH^(3/4));
+disp(NS,"the dimensionless specific speed is")
diff --git a/2223/CH14/EX14.2/Ex14_2.sav b/2223/CH14/EX14.2/Ex14_2.sav
new file mode 100755
index 000000000..667d9fe06
--- /dev/null
+++ b/2223/CH14/EX14.2/Ex14_2.sav
diff --git a/2223/CH14/EX14.2/Ex14_2.sce b/2223/CH14/EX14.2/Ex14_2.sce
new file mode 100755
index 000000000..aa25a1540
--- /dev/null
+++ b/2223/CH14/EX14.2/Ex14_2.sce
@@ -0,0 +1,14 @@
+// scilab Code Exa 14.2 Downstream guide vanes
+
+beta3=10; // rotor blade air angle at exit in degree
+dh=0.3; // hub diameter in m
+dt=0.6; // tip diameter in m
+N=960; // rotor Speed in RPM
+phi=0.245; // flow coefficient
+d=0.5*(dt+dh);
+u=%pi*d*N/60;
+cx=phi*u;
+cy3=u-(cx*tand(beta3));
+alpha3=atand(cy3/cx);
+disp("the rotor blade air angles, overall efficiency, flow rate, power required and degree of reaction are the same as calculated in Ex14_1")
+disp("degree",alpha3,"the guide vane air angle at the entry alpha3=")
diff --git a/2223/CH14/EX14.3/Ex14_3.sav b/2223/CH14/EX14.3/Ex14_3.sav
new file mode 100755
index 000000000..84929a688
--- /dev/null
+++ b/2223/CH14/EX14.3/Ex14_3.sav
diff --git a/2223/CH14/EX14.3/Ex14_3.sce b/2223/CH14/EX14.3/Ex14_3.sce
new file mode 100755
index 000000000..1be6349e4
--- /dev/null
+++ b/2223/CH14/EX14.3/Ex14_3.sce
@@ -0,0 +1,43 @@
+// scilab Code Exa 14.3 upstream guide vanes
+beta2=86; // rotor blade air angle at inlet in degree
+dh=0.3; // hub diameter in m
+dt=0.6; // tip diameter in m
+N=960; // rotor Speed in RPM
+phi=0.245; // flow coefficient
+T1=316;  // in Kelvin
+p1=1.02; //Initial Pressure in bar
+R=287;
+n_o=0.647; // overall Efficiency of the drive
+A=%pi*((dt^2)-(dh^2))/4;
+d=0.5*(dt+dh);
+u=%pi*d*N/60;
+cx=phi*u;
+Q=cx*A;
+ro=(p1*1e5)/(R*T1);
+
+// part(i) static pressure rise in the rotor and stage
+delh0_st=(u^2)*((phi*(tand(beta2)))-1);
+delp0_st=ro*delh0_st;
+disp("mm W.G.",delp0_st/9.81,"(i)static pressure rise in the stage is")
+beta3=atand(u/cx);
+w2=cx/(cosd(beta2));
+w3=cx/(cosd(beta3));
+delp_r=0.5*ro*((w2^2)-(w3^2));
+disp("mm W.G.",delp_r/9.81,"and the static pressure rise in the rotor is")
+
+// part(ii) the stage pressure coefficient and degree of reaction
+shi=2*((phi*(tand(beta2)))-1);
+disp(shi,"(ii)stage pressure coefficient is")
+DOR=0.5*((phi*(tand(beta2)))+1);
+disp("%",DOR*1e2,"and the degree of reaction is") 
+
+// part(iii) the blade air angle at the rotor exit and the air angle at the UGV exit
+disp("degree",beta3,"(iii)the blade air angle at the rotor exit beta3=")
+cy2=(cx*tand(beta2))-u;
+alpha2=atand(cy2/cx);
+disp("degree",alpha2,"and the air angle at the UGV exit alpha2=")
+
+// part(iv) Power required to drive the fan
+m=ro*Q;
+P=m*delh0_st/n_o;
+disp("kW",P/1000,"(iv)Power required to drive the fan is")
diff --git a/2223/CH14/EX14.4/Ex14_4.sav b/2223/CH14/EX14.4/Ex14_4.sav
new file mode 100755
index 000000000..0175d013b
--- /dev/null
+++ b/2223/CH14/EX14.4/Ex14_4.sav
diff --git a/2223/CH14/EX14.4/Ex14_4.sce b/2223/CH14/EX14.4/Ex14_4.sce
new file mode 100755
index 000000000..579dfc88c
--- /dev/null
+++ b/2223/CH14/EX14.4/Ex14_4.sce
@@ -0,0 +1,27 @@
+// scilab Code Exa 14.4 rotor and upstream guide blades
+beta2=30; // rotor blade air angle at inlet in degree
+beta3=10; // rotor blade air angle at exit in degree
+dh=0.3; // hub diameter in m
+dt=0.6; // tip diameter in m
+N=960; // rotor Speed in RPM
+phi=0.245; // flow coefficient
+T1=316;  // in Kelvin
+p1=1.02; //Initial Pressure in bar
+R=287;
+n_d=0.88; // Efficiency of the drive
+n_f=0.8; // Efficiency of the fan
+A=%pi*((dt^2)-(dh^2))/4;
+d=0.5*(dt+dh);
+u=%pi*d*N/60;
+cx=phi*u;
+Q=cx*A;
+ro=(p1*1e5)/(R*T1);
+delh0_st=(u^2)*phi*(tand(beta2)-tand(beta3));
+n_o=n_f*n_d;
+delp0_st=n_f*ro*delh0_st;
+disp("mm W.G.",delp0_st/9.81,"static pressure rise in the stage is")
+shi=2*phi*(tand(beta2)-tand(beta3));
+disp(shi,"stage pressure coefficient is")
+m=ro*Q;
+P=m*delh0_st/n_d;
+disp("kW",P/1000,"Power required to drive the fan is")
diff --git a/2223/CH14/EX14.5/Ex14_5.sav b/2223/CH14/EX14.5/Ex14_5.sav
new file mode 100755
index 000000000..98d440119
--- /dev/null
+++ b/2223/CH14/EX14.5/Ex14_5.sav
diff --git a/2223/CH14/EX14.5/Ex14_5.sce b/2223/CH14/EX14.5/Ex14_5.sce
new file mode 100755
index 000000000..730b5ff97
--- /dev/null
+++ b/2223/CH14/EX14.5/Ex14_5.sce
@@ -0,0 +1,26 @@
+// scilab Code Exa 14.5 DGVs and upstream guide vanes
+beta2=86; // rotor blade air angle at inlet in degree
+beta3=10; // rotor blade air angle at exit in degree
+dh=0.3; // hub diameter in m
+dt=0.6; // tip diameter in m
+N=960; // rotor Speed in RPM
+phi=0.245; // flow coefficient
+T1=316;  // in Kelvin
+p1=1.02; //Initial Pressure in bar
+R=287;
+n_d=0.8; // Efficiency of the drive
+n_f=0.85; // Efficiency of the fan
+A=%pi*((dt^2)-(dh^2))/4;
+d=0.5*(dt+dh);
+u=%pi*d*N/60;
+cx=phi*u;
+Q=cx*A;
+ro=(p1*1e5)/(R*T1);
+delh0_st=2*(u^2)*((phi*(tand(beta2)))-1);
+delp0_st=n_f*ro*delh0_st;
+disp("mm W.G.",delp0_st/9.81,"static pressure rise in the stage is")
+shi=4*((phi*(tand(beta2)))-1);
+disp(shi,"stage pressure coefficient is")
+m=ro*Q;
+P=m*delh0_st/n_d;
+disp("kW",P/1000,"Power of the electric motor is")
diff --git a/2223/CH14/EX14.6/Ex14_6.sav b/2223/CH14/EX14.6/Ex14_6.sav
new file mode 100755
index 000000000..4456c90a5
--- /dev/null
+++ b/2223/CH14/EX14.6/Ex14_6.sav
diff --git a/2223/CH14/EX14.6/Ex14_6.sce b/2223/CH14/EX14.6/Ex14_6.sce
new file mode 100755
index 000000000..447427006
--- /dev/null
+++ b/2223/CH14/EX14.6/Ex14_6.sce
@@ -0,0 +1,20 @@
+// scilab Code Exa 14.6 open propeller fan
+c_u=5; // upstream velocity in m/s
+c_s=25; // downstream velocity in m/s
+t=37; // in degree C
+T=t+273; // in Kelvin
+d=0.5;
+p=1.02; // Initial Pressure in bar
+R=287;
+n_o=0.4; // overall Efficiency of the fan
+A=%pi*(d^2)/4;
+c=0.5*(c_u+c_s);
+Q=c*A;
+ro=(p*1e5)/(R*T);
+m=ro*c*A;
+disp("kg/s",m,"(a) flow rate through the fan is")
+delh_0=0.5*((c_s^2)-(c_u^2));
+delp_0=ro*delh_0;
+disp("mm W.G.",delp_0/9.81,"(b)static pressure rise in the stage is")
+P=m*delh_0/n_o;
+disp("kW",P/1000,"(c)Power required to drive the fan is")
diff --git a/2223/CH15/EX15.1/Ex15_1.sav b/2223/CH15/EX15.1/Ex15_1.sav
new file mode 100755
index 000000000..84718f24a
--- /dev/null
+++ b/2223/CH15/EX15.1/Ex15_1.sav
diff --git a/2223/CH15/EX15.1/Ex15_1.sce b/2223/CH15/EX15.1/Ex15_1.sce
new file mode 100755
index 000000000..3c9e0274b
--- /dev/null
+++ b/2223/CH15/EX15.1/Ex15_1.sce
@@ -0,0 +1,23 @@
+// scilab Code Exa 15.1 Centrifugal fan stage 1450 rpm
+
+d1=0.18; // inner diameter of the impeller in m
+d2=0.2; // outer diameter of the impeller in m
+N=1450; // rotor Speed in RPM
+c1=21; // Absolute velocity at entry in m/s
+w1=20; // relative velocity at entry in m/s
+c2=25; // Absolute velocity at exit in m/s
+w2=17; // relative velocity at exit in m/s
+m=0.5; // flow rate in kg/s
+n_m=0.78; // overall Efficiency of the motor
+ro=1.25; // density of air in kg/m3
+
+u1=%pi*d1*N/60;
+u2=%pi*d2*N/60;
+delp_r=0.5*ro*((w1^2)-(w2^2))+(0.5*ro*((u2^2)-(u1^2)));
+delp0_st=0.5*ro*(((w1^2)-(w2^2))+((u2^2)-(u1^2))+((c2^2)-(c1^2)));
+disp("mm W.G.",delp0_st/9.81,"(a)stage pressure rise is")
+DOR=delp_r/delp0_st;
+disp(DOR,"(b)the degree of reaction is") 
+w_st=delp0_st/ro;
+P=m*w_st/n_m;
+disp("W",P,"(c)the motor Power required to drive the fan is")
diff --git a/2223/CH15/EX15.2/Ex15_2.sav b/2223/CH15/EX15.2/Ex15_2.sav
new file mode 100755
index 000000000..314e19ae5
--- /dev/null
+++ b/2223/CH15/EX15.2/Ex15_2.sav
diff --git a/2223/CH15/EX15.2/Ex15_2.sce b/2223/CH15/EX15.2/Ex15_2.sce
new file mode 100755
index 000000000..bbbe14866
--- /dev/null
+++ b/2223/CH15/EX15.2/Ex15_2.sce
@@ -0,0 +1,48 @@
+// scilab Code Exa 15.2 Centrifugal blower 3000 rpm
+
+beta2=90; // rotor blade air angle at inlet in degree
+N=3e3; // rotor Speed in RPM
+T1=310;  // in Kelvin
+p1=0.98; //Initial Pressure in bar
+R=287;
+n_d=0.88; // Efficiency of the drive
+n_f=0.82; // Efficiency of the fan
+Q=200/60; // discharge in m3/s
+h=1000; // mm column of water
+delp0=h*9.81;
+Pi=Q*delp0/1000; // ideal power
+P=Pi/(n_d*n_f);
+disp("kW",P,"(a)Power required by the electric motor is")
+
+// part(b) impeller diameter
+ro=(p1*1e5)/(R*T1);
+u2=sqrt(delp0/(ro*n_f));
+d2=u2*60/(%pi*N);
+disp("cm",d2*1e2,"(b)the impeller diameter is")
+
+// part(c) inner diameter of the blade ring
+c_r2=0.2*u2;
+c_i=0.4*u2;
+d1=sqrt(Q*4/(%pi*c_i));
+disp("cm",d1*1e2,"(c)the inner diameter of the blade ring is")
+
+// part(d) air angle at the entry
+u1=u2*d1/d2;
+beta1=atand(c_r2/u1);
+disp("degree",beta1,"(d)the air angle at the entry beta1=")
+
+// part(e) impeller widths at entry and exit
+b1=Q/(c_r2*%pi*d1);
+disp("cm",b1*1e2,"(e)the impeller width at entry is")
+b2=b1*d1/d2;
+disp("cm",b2*1e2,"and the impeller width at exit is")
+
+// part(f) number of impeller blades
+z=8.5*sind(beta2)/(1-(d1/d2));
+disp(z,"(f)the number of impeller blades is")
+
+// part(g) the specific speed
+gH=u2^2;
+omega=2*%pi*N/60;
+NS=omega*sqrt(Q)/(gH^(3/4));
+disp(NS,"(g)the dimensionless specific speed is")
diff --git a/2223/CH16/EX16.1/Ex16_1.sav b/2223/CH16/EX16.1/Ex16_1.sav
new file mode 100755
index 000000000..696428033
--- /dev/null
+++ b/2223/CH16/EX16.1/Ex16_1.sav
diff --git a/2223/CH16/EX16.1/Ex16_1.sce b/2223/CH16/EX16.1/Ex16_1.sce
new file mode 100755
index 000000000..075e0da01
--- /dev/null
+++ b/2223/CH16/EX16.1/Ex16_1.sce
@@ -0,0 +1,25 @@
+// scilab Code Exa 16.1 Wind turbine output 100 kW
+
+c_u=48*5/18; // wind upstream velocity in m/s
+n=0.95; // overall Efficiency of the drive
+P=100; // aerogenerator power output in kW
+n_m=0.9; // mechanical Efficiency of the drive
+n_a=0.7; // aerodynamic Efficiency
+ro=1.125; // density of air in kg/m3
+cp_max=0.593; // power coefficient for the windmill(Pi/Pu)
+
+// part(a) propeller diameter of the windmill
+A=2*P*1e3/(ro*(c_u^3)*n*n_m*n_a*cp_max);
+d=sqrt(4*A/%pi);
+disp("m",d,"(a)the propeller diameter of the windmill is")
+
+// part(b)
+disp("(b)corresponding to maximum power")
+c=2*c_u/3;
+disp("m/s",c,"the wind velocity through the propeller disc is")
+delp1_a=5*ro*(c^2)/8;
+disp("mm W.G.",delp1_a/9.81,"the gauge pressure just before the disc is")
+delp2_a=-3*ro*(c^2)/8;
+disp("mm W.G.",delp2_a/9.81,"the gauge pressure just after the disc is")
+Fx=(delp1_a-delp2_a)*A;
+disp("kN",Fx*1e-3,"and the axial thrust is")
diff --git a/2223/CH18/EX18.1/Ex18_1.sav b/2223/CH18/EX18.1/Ex18_1.sav
new file mode 100755
index 000000000..9bd7e8796
--- /dev/null
+++ b/2223/CH18/EX18.1/Ex18_1.sav
diff --git a/2223/CH18/EX18.1/Ex18_1.sce b/2223/CH18/EX18.1/Ex18_1.sce
new file mode 100755
index 000000000..6019def92
--- /dev/null
+++ b/2223/CH18/EX18.1/Ex18_1.sce
@@ -0,0 +1,43 @@
+// scilab Code Exa 18.1 Gas Turbine nozzle row 
+
+T1=600;  // Entry Temperature of the gas in Kelvin
+p1=10; // Inlet Pressure in bar
+gamma_g=1.3;
+delT=32; // Temperature drop of the gas(T1-T2) in K
+cp_g=1.23*1e3; // Specific Heat of gas at Constant Pressure in kJ/(kgK)
+pr1_2=1.3; // pressure ratio(p1/p2)
+T2s=T1/(pr1_2^((gamma_g-1)/gamma_g));
+delTs=T1-T2s;
+
+// part(a) nozzle efficiency
+n_N=delT/delTs;
+disp("%",n_N*100,"(a) nozzle efficiency is")
+
+// part(b)
+disp("(b)(i)for ideal flow:")
+p2=p1/pr1_2;
+h_01=cp_g*T1;
+h2s=cp_g*T2s;
+c_2s=sqrt((h_01-h2s)/0.5);
+disp("m/s",c_2s,"the nozzle exit velocity is")
+R_g=cp_g*((gamma_g-1)/gamma_g);
+M_2s=c_2s/(sqrt(gamma_g*R_g*T2s));
+disp(M_2s,"and the Mach number is")
+disp("(b)(ii)for actual flow:")
+T2=T1-delT;
+a2=sqrt(gamma_g*R_g*T2);
+c_2=sqrt((cp_g*delT)/0.5);
+disp("m/s",c_2,"the nozzle exit velocity is")
+M2=c_2/a2;
+disp(M2,"and the Mach number is")
+
+// part(c) stagnation pressure loss across the nozzle
+p01=p1;
+p02=p2/0.79; // from isentropic gas tables p2/p02=0.79 at gamma=1.3 and M2=0.613
+delp0=p01-p02;
+disp("bar",delp0,"(c)the stagnation pressure loss across the nozzle is")
+
+// part(d) nozzle efficiency based on stagnation pressure loss
+delp=p1-p2;
+n_N_a=1-(delp0/delp);
+disp("%",n_N_a*100,"(d)the nozzle efficiency based on stagnation pressure loss is")
diff --git a/2223/CH18/EX18.10/Ex18_10.sav b/2223/CH18/EX18.10/Ex18_10.sav
new file mode 100755
index 000000000..52ff1d432
--- /dev/null
+++ b/2223/CH18/EX18.10/Ex18_10.sav
diff --git a/2223/CH18/EX18.10/Ex18_10.sce b/2223/CH18/EX18.10/Ex18_10.sce
new file mode 100755
index 000000000..b3df9356c
--- /dev/null
+++ b/2223/CH18/EX18.10/Ex18_10.sce
@@ -0,0 +1,54 @@
+// scilab Code Exa 18.10 Calculation on combined cycle power plant
+
+P_gt=25.845; // Power Output of gas turbine plant in MW
+P_st=21; // Power Output of steam turbine plant in MW
+m_gt=115; // mass flow rate of the exhaust gas in kg/s
+n_T=0.86; // Turbine Efficiency
+gamma_g=1.33;
+R=0.287;
+cp=(gamma_g/(gamma_g-1))*R; // Specific Heat at Constant Pressure in kJ/(kgK)
+T3=1341; // Maximum Temperature in gas turbine in degree K from Ex18.9
+p1=84; // steam Pressure at the entry of steam turbine in bar
+// from steam tables
+t_6s=298.4; // saturation temperature at 84 bar in degree C
+t_5s=t_6s;
+h_6s=1336.1; // from steam table liquid vapour enthalpy at 84 bar
+t6=535;  // steam temperature at the entry of steam turbine in degree C
+T6=t6+273; // in Kelvin
+h_4s=3460; // from mollier diagram at t=535 degree C
+h_7=2050;
+p_c=0.07; // Condenser pressure in bar
+r=8.8502464; //optimum pressure ratio from Ex18.9
+T4=875.92974; //from Ex 18.9
+t4=T4-273; // in degree C
+h_7s=163.4; // Specific Enthalpy of water in kJ/kg
+m_st=P_st*1e3/((h_4s-h_7)*n_T); // mass flow rate of the steam in kg/s
+
+// part(a)Exhaust gas temperature at stack
+t_7=t4-((m_st*(h_4s-h_7s))/(m_gt*cp)); // energy balance for the economiser entry(7') to the superheater exit(4')
+disp("degree celsius",t_7,"(a)Exhaust gas temperature at stack is")
+
+// part(b)mass of steam per kg of gas
+disp("kg",m_st/m_gt,"(b)mass of steam per kg of gas is")
+
+// part(c) Pinch Point(PP)
+t_6=t_7+((m_st*(h_6s-h_7s))/(m_gt*cp)); // energy balance for the economiser
+PP=t_6-t_6s;
+disp("degree celsius",PP,"(c)Pinch Point(PP) is")
+
+// part(d)thermal efficiency of steam turbine plant
+delh4s_7ss=(h_4s-h_7)*n_T;
+n_st=delh4s_7ss/(h_4s-h_7s);
+disp("%",n_st*100,"(d)thermal Efficiency of steam turbine plant is")
+
+// part(e) thermal efficiency of the combined cycle plant
+n_B=0.978; // Assuming Combustion chamber Efficiency
+Qs=102.72554; // heat supplied in the combustion chamber from Ex 18.9
+Qss=Qs/n_B; // power supplied to the combined cycle
+n_gst=(P_gt+P_st)/Qss;
+disp ("%" ,n_gst*100,"(e)thermal Efficiency of combined gas and steam power plant is")
+
+// part(f)the dryness fraction of steam at the turbine exhaust
+x=0.875; // from Mollier diagram at p=0.07 bar
+disp(x,"(f)the dryness fraction of steam at the turbine exhaust is")
+
diff --git a/2223/CH18/EX18.11/Ex18_11.sav b/2223/CH18/EX18.11/Ex18_11.sav
new file mode 100755
index 000000000..48ba54185
--- /dev/null
+++ b/2223/CH18/EX18.11/Ex18_11.sav
diff --git a/2223/CH18/EX18.11/Ex18_11.sce b/2223/CH18/EX18.11/Ex18_11.sce
new file mode 100755
index 000000000..b51e7b9e0
--- /dev/null
+++ b/2223/CH18/EX18.11/Ex18_11.sce
@@ -0,0 +1,55 @@
+// scilab Code Exa 18.11 Calculation on combined cycle power plant
+
+P_gt=25.845; // Power Output of gas turbine plant in MW
+P_st=21; // Power Output of steam turbine plant in MW
+m_gt=115; // mass flow rate of the exhaust gas in kg/s
+n_T=0.86; // Turbine Efficiency
+gamma_g=1.33;
+R=0.287;
+cp=(gamma_g/(gamma_g-1))*R; // Specific Heat at Constant Pressure in kJ/(kgK)
+T3=1341; // Maximum Temperature in gas turbine in degree K from Ex18.9
+p1=84; // steam Pressure at the entry of steam turbine in bar
+// from steam tables
+t_6s=298.4; // saturation temperature at 84 bar in degree C
+h_6s=1336.1; // from steam table liquid vapour enthalpy at 84 bar
+pp(1)=20; // pinch point in degree C
+pp(2)=28.2;
+pp(3)=35;
+
+for i=1:3
+    printf("\nfor PP=%d degree C\n",pp(i))
+t_6=t_6s+pp(i);
+h_4s=3460; // from mollier diagram at t=535 degree C
+h_7=2050;
+p_c=0.07; // Condenser pressure in bar
+T4=875.92974; //from Ex 18.9
+t4=T4-273; // in degree C
+h_7s=163.4; // Specific Enthalpy of water in kJ/kg
+
+// part(a)steam flow per kg of gas
+m_st_gt=cp*(t4-t_6)/(h_4s-h_6s); // steam flow per kg of gas
+disp("kg",m_st_gt,"(a)steam flow per kg of gas is")
+
+// part(b)Exhaust gas temperature at stack
+t_7=t_6-((m_st_gt*(h_6s-h_7s))/(cp)); // energy balance for the economiser entry(7') to the superheater exit(4')
+disp("degree celsius",t_7,"(b)Exhaust gas temperature at stack is")
+
+// part(c)steam turbine plant output
+h_7ss=2247;
+P_st=m_st_gt*m_gt*(h_4s-h_7ss);
+disp("MW",P_st/1e3,"(c)Power output of the steam turbine plant is")
+
+// part(d)thermal efficiency of steam turbine plant
+delh4s_7ss=(h_4s-h_7)*n_T;
+n_st=delh4s_7ss/(h_4s-h_7s);
+disp("%",n_st*100,"(d)thermal Efficiency of steam turbine plant is")
+
+// part(e) thermal efficiency of the combined cycle plant
+n_B=0.978; // Assuming Combustion chamber Efficiency
+Qs=102.72554; // heat supplied in the combustion chamber from Ex 18.9
+Qss=Qs/n_B; // power supplied to the combined cycle
+n_gst=(P_gt+(P_st*1e-3))/Qss;
+disp("%",n_gst*100,"(e)thermal Efficiency of combined gas and steam power plant is")
+end
+
+disp("Comment: Error in Textbook, Answers vary due to Round-off Errors")
diff --git a/2223/CH18/EX18.12/Ex18_12.sav b/2223/CH18/EX18.12/Ex18_12.sav
new file mode 100755
index 000000000..4bf49a244
--- /dev/null
+++ b/2223/CH18/EX18.12/Ex18_12.sav
diff --git a/2223/CH18/EX18.12/Ex18_12.sce b/2223/CH18/EX18.12/Ex18_12.sce
new file mode 100755
index 000000000..8645e5951
--- /dev/null
+++ b/2223/CH18/EX18.12/Ex18_12.sce
@@ -0,0 +1,35 @@
+// scilab Code Exa 18.12 turbo prop Gas Turbine Engine
+
+Ti=268.65; // in Kelvin
+n_C=0.8; // Compressor Efficiency
+c1=85; // entry velocity in m/s
+m=50; // mass flow rate of air in kg/s
+R=287;
+gamma=1.4; // Specific Heat Ratio
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+u=500/3.6; // speed of a turbo prop aircraft in m/s
+delT=225; // temperature rise through the compressor(T02-T01) in K
+pi=.701; // Initial Pressure in bar
+n_D=0.88; // inlet diffuser efficiency
+a_i=sqrt(gamma*R*Ti);
+Mi=u/a_i;
+Toi_i=1/0.965; // (Toi/Ti)from isentropic flow gas tables at Mi and gamma values
+T01=Ti*Toi_i;
+T1=T01-(0.5*(c1^2)/(cp*1e3));
+
+//part(a)
+T1s_i=1+n_D*((T1/Ti)-1); // (T1s/Ti)isentropic temperature ratio through the diffuser
+p1_i=T1s_i^(gamma/(gamma-1)); // (p1s/pi)isentropic pressure ratio
+p1=p1_i*pi;
+delp_D=p1-pi;
+disp("bar",delp_D,"(a)isentropic pressure rise through the diffuser is")
+
+// part(b) compressor pressure ratio
+T02s=T01+(delT*n_C);
+r_oc=(T02s/T01)^(gamma/(gamma-1)); //compressor pressure ratio(p02/p01)
+disp(r_oc,"(b)compressor pressure ratio is")
+
+// part(c)
+P=m*cp*delT;
+disp("MW",P*1e-3,"(c)power required to drive the compressor is")
+
diff --git a/2223/CH18/EX18.13/Ex18_13.sav b/2223/CH18/EX18.13/Ex18_13.sav
new file mode 100755
index 000000000..9641ce3e5
--- /dev/null
+++ b/2223/CH18/EX18.13/Ex18_13.sav
diff --git a/2223/CH18/EX18.13/Ex18_13.sce b/2223/CH18/EX18.13/Ex18_13.sce
new file mode 100755
index 000000000..9169fc8bd
--- /dev/null
+++ b/2223/CH18/EX18.13/Ex18_13.sce
@@ -0,0 +1,55 @@
+// scilab Code Exa 18.13 Turbojet Gas Turbine Engine
+
+T1=223.15; // in Kelvin
+n_C=0.75; // Compressor Efficiency
+c1=85; // entry velocity in m/s
+m=50; // mass flow rate of air in kg/s
+R=287;
+n_B=0.98; // Combustion chamber Efficiency
+Qf=43*1e3; // Calorific Value of fuel in kJ/kg;
+T03=1220;  // Turbine inlet stagnation temp in Kelvin
+n_T=0.8; // Turbine Efficiency
+gamma=1.4; // Specific Heat Ratio
+n_m=0.98; // Mechanical efficiency
+sigma=0.5; // flight to jet speed ratio(u/ce)
+n_N=0.98; // exhaust nozzle efficiency
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+u=886/3.6; // flight speed of a turbo prop aircraft in m/s
+delT=200; // temperature rise through the compressor(T02-T01) in K
+pi=.701; // Initial Pressure in bar
+n_D=0.88; // inlet diffuser efficiency
+a1=sqrt(gamma*R*T1);
+M1=u/a1; // Mach number at the compressor inlet
+T1_01=0.881; // (T1/T01)from isentropic flow gas tables at M1 and gamma values
+T01=T1/T1_01;
+T1=T01-(0.5*(c1^2)/(cp*1e3));
+
+// part(a) compressor pressure ratio
+T02s=T01+(delT*n_C);
+r_oc=(T02s/T01)^(gamma/(gamma-1)); //compressor pressure ratio(p02/p01)
+disp(r_oc,"(a)compressor pressure ratio is")
+
+// part(b)
+T02=T01+delT;
+f=((cp*T03)-(cp*T02))/((Qf*n_B)-(cp*T03)); // f=(ma/mf);energy balance in the combustion chamber 
+disp(1/f,"(b)Air-Fuel Ratio is")
+
+// part(c) turbine pressure ratio
+// turbine power input P_T=n_m*(ma+mf)*cp*(T03-T01)
+// power input to the compressor P_C=ma*cp*(T02-T01)
+T04s=T03-(delT/(n_m*n_T*(1+f))); // from energy balance P_T=P_C
+r_ot=(T03/T04s)^(gamma/(gamma-1)); //turbine pressure ratio(p03/p04)
+disp(r_ot,"(c)turbine pressure ratio is")
+
+// part(d)exhaust nozzle pressure ratio
+ce=u/sigma; // jet velocity at the exit of the exhaust nozzle
+T04=T03-(delT/(n_m*(1+f)));
+Te=T04-(0.5*(ce^2)/(cp*1e3));
+Tes=T04-((T04-Te)/n_N);
+r_N=(T04/Tes)^(gamma/(gamma-1)); //exhaust nozzle pressure ratio(p04/pe)
+disp(r_N,"(d)exhaust nozzle pressure ratio is")
+ae=sqrt(gamma*R*Te);
+Me=ce/ae; // Mach number
+disp(Me,"and the Mach Number is")
+
+
diff --git a/2223/CH18/EX18.15/Ex18_15.sav b/2223/CH18/EX18.15/Ex18_15.sav
new file mode 100755
index 000000000..17bd16a24
--- /dev/null
+++ b/2223/CH18/EX18.15/Ex18_15.sav
diff --git a/2223/CH18/EX18.15/Ex18_15.sce b/2223/CH18/EX18.15/Ex18_15.sce
new file mode 100755
index 000000000..f41e5fdbb
--- /dev/null
+++ b/2223/CH18/EX18.15/Ex18_15.sce
@@ -0,0 +1,35 @@
+// scilab code Exa 18.15 Impulse Steam Turbine 3000 rpm
+
+P=500; // Power Output in kW
+u=100; // peripheral speed of the rotor blades in m/s
+cy2=200; // whirl component of the absolute velocity at entry of the rotor
+cy3=0; // whirl component of the absolute velocity at exit of the rotor
+alpha2=65; // nozzle angle at exit
+n_st=0.69; // isentropic stage efficiency
+p2=8; // steam pressure at the exit of the first stage in bar
+t2=200; // steam temperature at the exit of the first stage in degree C
+N=3e3; // rotor Speed in RPM
+
+//part(a)Mean diameter of the stage
+d=u*60/(%pi*N);
+disp("m",d,"(a)Mean diameter of the stage is")
+
+// part(b)mass flow rate of the steam
+w_st=2*(u^2)*1e-3; // specific work
+m=P/w_st;
+disp("kg/s",m,"(b)mass flow rate of the steam is")
+
+// part(c)isentropic enthalpy drop
+delh_s=w_st/n_st;
+disp("kJ/kg",delh_s,"(c)isentropic enthalpy drop is")
+
+// part(d)rotor blade angles
+cx=cy2/(tand(alpha2));
+beta3=atand(u/cx);
+disp("degree",beta3,"(d)the rotor blade angles are beta2=beta3=")
+
+// part(e)blade height at the nozzle exit
+v_s2=0.2608; // from steam tables at p2=8bar and t2=200 degree C
+Q=m*v_s2;
+h=Q/(cx*%pi*d);
+disp("m",h,"(e)blade height at the nozzle exit is")
diff --git a/2223/CH18/EX18.16/Ex18_16.sav b/2223/CH18/EX18.16/Ex18_16.sav
new file mode 100755
index 000000000..bb522b9f8
--- /dev/null
+++ b/2223/CH18/EX18.16/Ex18_16.sav
diff --git a/2223/CH18/EX18.16/Ex18_16.sce b/2223/CH18/EX18.16/Ex18_16.sce
new file mode 100755
index 000000000..fa8bc7045
--- /dev/null
+++ b/2223/CH18/EX18.16/Ex18_16.sce
@@ -0,0 +1,33 @@
+// scilab Code Exa 18.16 large Centrifugal pump 1000rpm
+
+N=1e3; // rotor Speed in RPM
+H=45; // height in m
+ro=1e3;
+g=9.81; // Gravitational acceleration in m/s^2
+n_o=0.75; // overall Efficiency of the drive
+dr=2; // diameter ratio(d2/d1)
+phi=0.35; // flow coefficient(cr2/u2)
+Q=2.5; // discharge in m3/s
+
+//part(a)Power required to drive the pump
+P=(ro*Q*g*H)/(n_o);
+disp("kW",P*1e-3,"(a)Power required to drive the pump is")
+
+// part(b) impeller diameters at entry and exit
+u2=sqrt(g*H);
+w_p=u2^2;
+d2=u2*60/(%pi*N);
+disp("cm",d2*1e2,"(b)the impeller diameter at exit is")
+d1=d2/2;
+disp("cm",d1*1e2,"and the impeller diameter at entry is")
+
+//part(c) impeller width
+c_r2=phi*u2;
+b=Q/(c_r2*%pi*d2);
+disp("cm",b*1e2,"(c)the impeller width is")
+
+// part(d)impeller blade angle at the entry
+c_r1=Q/(b*%pi*d1);
+u1=u2/dr;
+beta1=atand(c_r1/u1);
+disp("degree",beta1,"(d)the impeller blade angle at the entry beta1=")
diff --git a/2223/CH18/EX18.17/Ex18_17.sav b/2223/CH18/EX18.17/Ex18_17.sav
new file mode 100755
index 000000000..6a90f531c
--- /dev/null
+++ b/2223/CH18/EX18.17/Ex18_17.sav
diff --git a/2223/CH18/EX18.17/Ex18_17.sce b/2223/CH18/EX18.17/Ex18_17.sce
new file mode 100755
index 000000000..ec87bb2c5
--- /dev/null
+++ b/2223/CH18/EX18.17/Ex18_17.sce
@@ -0,0 +1,45 @@
+// scilab Code Exa 18.17 three stage steam turbine
+
+t1=250;  // Initial Temperature in degree C
+n_T=0.75; // overall Efficiency of the turbine
+p1=10; //Initial Pressure in bar
+n_m=0.98; // Mechanical Efficiency
+m=5;
+N=1e3; // rotor Speed in RPM
+H=45; // height in m
+ro=1e3;
+g=9.81; // Gravitational acceleration in m/s^2
+Q=2.5; // discharge in m3/s
+
+P=(ro*Q*g*H)/(n_T);
+delh_T=P/(m*n_m*1e3);
+delh_st=delh_T/3;
+delh1_4ss=delh_T/n_T;
+
+//part(a)steam conditions
+h1=2940; // from Mollier diagram
+disp("(a)steam conditions at the turbine exit are:")
+h_4ss=h1-delh1_4ss;
+p4=1.2; // in bar
+disp("bar",p4,"pressure:")
+h4=2640;
+x4=0.98;
+t4=104.8; // in degree C
+disp("degree C",t4,"temperature:")
+disp(x4,"the dryness fraction is:")
+
+// part(b)stage Efficiencies
+h2=h1-delh_st;
+p2=5;
+h3=h2-delh_st;
+p3=2.5;
+h4=h3-delh_st;
+h2s=2795;
+h3s=2705;
+h4s=2605;
+n_st1=delh_st/(h1-h2s);
+n_st2=delh_st/(h2-h3s);
+n_st3=delh_st/(h3-h4s);
+disp ("%",n_st1*100,"(b)Efficiency of the first stage is")
+disp ("%",n_st2*100,"Efficiency of the second stage is")
+disp ("%",n_st3*100,"Efficiency of the third stage is")
diff --git a/2223/CH18/EX18.18/Ex18_18.sav b/2223/CH18/EX18.18/Ex18_18.sav
new file mode 100755
index 000000000..0cd6376c3
--- /dev/null
+++ b/2223/CH18/EX18.18/Ex18_18.sav
diff --git a/2223/CH18/EX18.18/Ex18_18.sce b/2223/CH18/EX18.18/Ex18_18.sce
new file mode 100755
index 000000000..02d6b436e
--- /dev/null
+++ b/2223/CH18/EX18.18/Ex18_18.sce
@@ -0,0 +1,27 @@
+// scilab Code Exa 18.18 Ljungstrom turbine 3600 rpm
+
+d1=0.92; // inner diameter of the impeller in m
+d2=1; // outer diameter of the impeller in m
+N=3.6e3; // rotor Speed in RPM
+aplha_1=20; // blade exit angle in degree
+p2=0.1; //exit Pressure of steam in bar
+x2=0.88; // dryness fraction at exit
+n_st=0.83; // stage Efficiency
+u1=%pi*d1*N/60;
+u2=%pi*d2*N/60;
+
+//part(a)power developed
+sigma=cosd(aplha_1)/2;
+w_st=u1^2+u2^2;
+disp("kW/(kg/s)",w_st*1e-3,"(a)power developed per unit flow rate is")
+
+//part(b) isentropic enthalpy drop
+delh_s=w_st/n_st;
+disp("kJ/kg",delh_s*1e-3,"(b)isentropic enthalpy drop is")
+
+// part(c)steam conditions at entry
+disp("(c)steam conditions at entry are:")
+p1=0.18; // in bar
+disp("bar",p1,"pressure:")
+x1=0.9;
+disp(x1,"the dryness fraction is:")
diff --git a/2223/CH18/EX18.19/Ex18_19.sav b/2223/CH18/EX18.19/Ex18_19.sav
new file mode 100755
index 000000000..8977a49e7
--- /dev/null
+++ b/2223/CH18/EX18.19/Ex18_19.sav
diff --git a/2223/CH18/EX18.19/Ex18_19.sce b/2223/CH18/EX18.19/Ex18_19.sce
new file mode 100755
index 000000000..9e580fc06
--- /dev/null
+++ b/2223/CH18/EX18.19/Ex18_19.sce
@@ -0,0 +1,46 @@
+// scilab Code Exa 18.19 blower type wind tunnel 
+
+T01=310;  // in Kelvin
+p01=1.013; //  Initial Pressure in bar
+n_n=0.96; // nozzle efficiency
+n_c=0.78; // compressor efficiency
+Ma(1)=0.5;
+Ma(2)=0.9;
+pi(1)=0.837; // from isentropic flow gas tables
+pi(2)=0.575;
+gamma=1.4; // Specific Heat Ratio
+R=287;
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+
+for i=1:2
+printf("when Ma=%f",Ma(i))
+//part(a)
+Ms=((n_n/(Ma(i)^2))-(((gamma-1)/2)*(1-n_n)))^(-1/2);
+disp(Ms,"(a)Mach number for isentropic flow is")
+
+// part(b)
+p0e=1;
+p_r0(i)=p0e/pi(i);
+disp(p_r0(i),"(b)pressure ratio of the compressor is")
+
+// part(c)
+delT0e_0i=((p_r0(i)^((gamma-1)/gamma))-1)/n_c;
+T0e=T01+(T01*delT0e_0i);
+delT0e_t=n_n*(1-(p_r0(i)^((1-gamma)/gamma)))*T0e;
+T_t=T0e-delT0e_t;
+disp("K",T_t,"(c)the test section temperature is")
+a_t=sqrt(gamma*R*T_t);
+c_t=Ma(i)*a_t;
+disp("m/s",c_t,"and the test section velocity is")
+
+// part(d)
+ro_t=p01*1e5/(R*T_t);
+A_t=0.17*0.15;
+m=ro_t*A_t*c_t;
+disp("kg/s",m,"(d)mass flow rate is")
+
+// part(e)
+P(1)=m*cp*(T0e-T01);
+P(2)=m*cp*(T_t-T01);
+disp("kW",P(i),"(e)power required for the compressor is")
+end
diff --git a/2223/CH18/EX18.2/Ex18_2.sav b/2223/CH18/EX18.2/Ex18_2.sav
new file mode 100755
index 000000000..14e8076cc
--- /dev/null
+++ b/2223/CH18/EX18.2/Ex18_2.sav
diff --git a/2223/CH18/EX18.2/Ex18_2.sce b/2223/CH18/EX18.2/Ex18_2.sce
new file mode 100755
index 000000000..4796516bf
--- /dev/null
+++ b/2223/CH18/EX18.2/Ex18_2.sce
@@ -0,0 +1,38 @@
+// scilab Code Exa 18.2 Steam Turbine nozzle 
+
+t1=550;  // Entry Temperature in Kelvin
+p1=170; // Inlet Pressure in bar
+p2=120.7; // Exit Pressure in bar
+d=1; // Mean Blade ring diameter in m
+alpha_2=70;  // nozzle angle in degree
+gamma_g=1.3; // for superheated steam
+R=0.5*1e3; // in J/kgK
+m=280; // in kg/s
+
+// part(a) exit velocity c2 of steam
+h1=3440; // from superheated steam tables at p1 and t1
+h2=3350; // at p2
+t2=503; // at p2 in degree C
+v_s2=0.0268; // Specific Volume at p2 in m3/kg
+c_2=sqrt((h1-h2)*1e3/0.5);
+disp("m/s",c_2,"(a)the nozzle exit velocity is")
+
+// part(b)
+T2=t2+273;
+a2=sqrt(gamma_g*R*T2);
+M2=c_2/a2;
+disp(M2,"(b)and the exit Mach number is")
+
+// part(c)
+cx=c_2*cosd(alpha_2);
+h=m*v_s2/(%pi*cx*d);
+disp("cm",h*1e2,"(c)nozzle blade height at exit is")
+
+T2s=0.87*(t1+273); // T2s/T1=0.87 from gas tables
+p2s=0.546*p1; // p2s/p1=0.546 from gas tables
+vs_s=0.031; // from steam tables
+a_s=sqrt(gamma_g*R*T2s);
+disp("m/s",a_s,"the corresponding nozzle exit velocity is")
+cx_s=a_s*cosd(alpha_2);
+m_max=cx_s*%pi*d*h/(vs_s);
+disp("kg/s",m_max,"the maximum possible mass flow rate is")
diff --git a/2223/CH18/EX18.20/Ex18_20.sav b/2223/CH18/EX18.20/Ex18_20.sav
new file mode 100755
index 000000000..1783b434b
--- /dev/null
+++ b/2223/CH18/EX18.20/Ex18_20.sav
diff --git a/2223/CH18/EX18.20/Ex18_20.sce b/2223/CH18/EX18.20/Ex18_20.sce
new file mode 100755
index 000000000..fc5844b8b
--- /dev/null
+++ b/2223/CH18/EX18.20/Ex18_20.sce
@@ -0,0 +1,37 @@
+// scilab Code Exa 18.20 Calculation on an axial turbine cascade
+
+beta1=35; //  blade angle at entry
+beta2=55; // blade angle at exit
+i(1)=5; // incidence
+i(2)=10;
+i(3)=15;
+i(4)=20;
+delta=2.5; // deviation
+alpha2=beta2-delta; // air angle at exit
+a_r=2.5; // aspect ratio(h/l)
+
+n=4;
+for m=1:n
+//part(a)
+printf("\nfor incidence=%d\n",i(m))
+alpha1=beta1+i(m); // air angle at entry
+ep=alpha1+alpha2; // deflection angle
+disp("degree",ep,"(a)flow deflection is")
+p_c=0.505; //(s/l)
+
+//part(b) loss coefficient from Hawthorne relations
+
+z_p=0.025*(1+((ep/90)^2)); // Hawthorne's relation
+disp (z_p,"(b)the profile loss coefficient from Hawthorne relation is")
+z=(1+(3.2/a_r))*z_p; // the total cascade loss coefficient
+disp (z,"and the total loss coefficient is")
+Y=z; 
+
+// part(c)drag and lift coefficients
+alpham=atand((0.5*(tand(alpha2)-tand(alpha1))));
+C_D=p_c*Y*((cosd(alpham)^3)/(cosd(alpha2)^2));
+disp (C_D,"(c)the drag coefficient is")
+
+C_L=(2*p_c*(tand(alpha1)+tand(alpha2))*cosd(alpham))+(C_D*tand(alpham));
+disp (C_L,"and the Lift coefficient is")
+end
diff --git a/2223/CH18/EX18.21/Ex18_21.sav b/2223/CH18/EX18.21/Ex18_21.sav
new file mode 100755
index 000000000..0e53cfe52
--- /dev/null
+++ b/2223/CH18/EX18.21/Ex18_21.sav
diff --git a/2223/CH18/EX18.21/Ex18_21.sce b/2223/CH18/EX18.21/Ex18_21.sce
new file mode 100755
index 000000000..222160efb
--- /dev/null
+++ b/2223/CH18/EX18.21/Ex18_21.sce
@@ -0,0 +1,43 @@
+// scilab Code Exa 18.21 low reaction turbine stage
+
+Beta2=35; // rotor blade air angle in degree
+alpha1=0; // fixed blade air angle in degree
+alpha2=65;
+beta3=52.5;
+I(1)=0; // incidence angle
+I(2)=5;
+I(3)=10;
+I(4)=15;
+I(5)=20;
+a_r=2.5; // aspect ratio(h/l)
+
+for i=1:5
+disp("degree",I(i),"when incidence=")
+beta2(i)=Beta2+I(i); // beta2 varies with incidence
+
+//part(a)
+phi=cosd(alpha2)*cosd(beta2(i))/(sind(alpha2-beta2(i)));
+ep=alpha1+alpha2; // deflection angle
+disp(phi,"(a)flow coefficient is")
+p_c=0.505; //pitch-chord ratio(s/l)
+
+//part(b)blade to gas speed ratio
+sigma=sind(alpha2-beta2(i))/(cosd(beta2(i)));
+disp(sigma,"(b)blade to gas speed ratio is")
+z_N=2.28*0.025*(1+((ep/90)^2)); // Hawthorne's relation
+
+// part(c)degree of reaction
+R=0.5*phi*(tand(beta3)-tand(beta2(i)));
+disp("%",R*1e2,"(c)the degree of reaction is")
+
+// part(d)total-to-total efficiency
+e_R=beta2(i)+beta3; // Rotor deflection angle
+zeeta_p_R=0.025*(1+((e_R/90)^2)); // profile loss coefficient for rotor
+zeeta_R=(1+(3.2/a_r))*zeeta_p_R; // total loss coefficient for rotor
+a=(zeeta_R*(secd(beta3)^2))+(z_N*(secd(alpha2)^2));
+b=phi*(tand(alpha2)+tand(beta3))-1;
+n_tt=inv(1+(0.5*(phi^2)*(a/b)));
+disp("%",n_tt*1e2,"(d)total-to-total efficiency is")
+
+end
+
diff --git a/2223/CH18/EX18.22/Ex18_22.sav b/2223/CH18/EX18.22/Ex18_22.sav
new file mode 100755
index 000000000..2fe4d5990
--- /dev/null
+++ b/2223/CH18/EX18.22/Ex18_22.sav
diff --git a/2223/CH18/EX18.22/Ex18_22.sce b/2223/CH18/EX18.22/Ex18_22.sce
new file mode 100755
index 000000000..e42240371
--- /dev/null
+++ b/2223/CH18/EX18.22/Ex18_22.sce
@@ -0,0 +1,29 @@
+// scilab Code Exa 18.22 Isentropic or Stage Terminal Velocity for Turbines 
+
+T01=1273;  // in Kelvin
+funcprot(0);
+p01=5; //  Initial Pressure in bar
+p02=3.5; //  exit gas Pressure in bar
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+gamma=1.4; // Specific Heat Ratio
+m=28; // mass flow rate of the gas in kg/s
+n_tt=0.84; // stage efficiency
+shi=1.7; // stage loading coefficient
+pr_0=p01/p02;
+delh01_03ss=cp*T01*(1-(pr_0^((1-gamma)/gamma)));
+
+//part(a)stage terminal velocity
+c0=sqrt(2*delh01_03ss*1e3);
+disp("m/s",c0,"(a)stage terminal velocity is")
+
+// part(b)isentropic blade to gas speed ratio
+sigma_s=sqrt(0.5*n_tt/shi);
+disp(sigma_s,"(b)the isentropic blade to gas speed ratio is")
+
+//part(c) peripheral speed of the rotor
+u=sigma_s*c0;
+disp("m/s",u,"(c)peripheral speed of the rotor is")
+
+//part(d) the power developed
+P=m*n_tt*delh01_03ss;
+disp("MW",P*1e-3,"(d) the power developed is")
diff --git a/2223/CH18/EX18.23/Ex18_23.sav b/2223/CH18/EX18.23/Ex18_23.sav
new file mode 100755
index 000000000..8726c784d
--- /dev/null
+++ b/2223/CH18/EX18.23/Ex18_23.sav
diff --git a/2223/CH18/EX18.23/Ex18_23.sce b/2223/CH18/EX18.23/Ex18_23.sce
new file mode 100755
index 000000000..25c0e7072
--- /dev/null
+++ b/2223/CH18/EX18.23/Ex18_23.sce
@@ -0,0 +1,7 @@
+// scilab Code Exa 18.23 axial compressor stage efficiency 
+
+R=0.5; // Degree of reaction
+n_R=0.849; // efficiency of rotor blade row
+n_D=0.849; // efficiency of diffuser blade row
+n_st=R*n_R+(1-R)*n_D;
+disp("%",n_st*1e2,"the value of stage efficiency is")
diff --git a/2223/CH18/EX18.24/Ex18_24.sav b/2223/CH18/EX18.24/Ex18_24.sav
new file mode 100755
index 000000000..d74e6eadb
--- /dev/null
+++ b/2223/CH18/EX18.24/Ex18_24.sav
diff --git a/2223/CH18/EX18.24/Ex18_24.sce b/2223/CH18/EX18.24/Ex18_24.sce
new file mode 100755
index 000000000..097fe2599
--- /dev/null
+++ b/2223/CH18/EX18.24/Ex18_24.sce
@@ -0,0 +1,17 @@
+// scilab Code Exa 18.24 Calculation on an axial compressor cascade 
+
+beta1=51;
+beta2=9;
+alpha_1=7;  //  air angle at rotor and stator exit
+u=100; // test section velocity of air in m/s
+cx=u/(tand(alpha_1)+tand(beta1));
+w1=cx/cosd(beta1);
+alpha2=atand(tand(alpha_1)+tand(beta1)-tand(beta2))
+c2=cx/cosd(alpha2);
+Y_D=0.0367; // loss coefficient for diffuser blade row
+Y_R=0.0393; // loss coefficient for rotor blade row
+z_R=Y_R*((w1/u)^2);
+z_D=Y_D*((c2/u)^2);
+phi=cx/u;
+n_st=1-(0.5*phi*(z_D*(secd(alpha2)^2)+z_R*(secd(beta1)^2))/(tand(beta1)-tand(beta2)));
+disp("%",n_st*1e2,"the value of stage efficiency is")
diff --git a/2223/CH18/EX18.25/Ex18_25.sav b/2223/CH18/EX18.25/Ex18_25.sav
new file mode 100755
index 000000000..669d86539
--- /dev/null
+++ b/2223/CH18/EX18.25/Ex18_25.sav
diff --git a/2223/CH18/EX18.25/Ex18_25.sce b/2223/CH18/EX18.25/Ex18_25.sce
new file mode 100755
index 000000000..c6627cef7
--- /dev/null
+++ b/2223/CH18/EX18.25/Ex18_25.sce
@@ -0,0 +1,74 @@
+// scilab Code Exa 18.25 Calculation on two stage axial compressor 
+
+T01=310;  // in Kelvin
+funcprot(0);
+gamma=1.4;
+p01=1.02; //  Initial Pressure in bar
+pr_o=2;
+pr_o1=1.5;
+N=7.2e3; // rotor Speed in RPM
+d=65/100; // Mean Blade ring diameter in m
+h=10/100; // blade height at entry in m
+n_p=0.9; // polytropic efficiency
+wdf=0.87; // work-done factor
+m=25; //  in kg/s 
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+R=287;
+T01(1)=T01;
+// part(a) stage pressure ratio
+pr_o2=pr_o/pr_o1;
+disp(pr_o2,"(a)pressure ratio developed by the 2nd stage is")
+
+//part(b) stage efficiency
+n=(gamma-1)/gamma;
+n_st1=((pr_o1^n)-1)/((pr_o1^(n/n_p))-1);
+disp("%",n_st1*1e2,"(b)stage efficiency for the stage 1 is")
+n_st2=((pr_o2^n)-1)/((pr_o2^(n/n_p))-1);
+disp("%",n_st2*1e2,"and stage efficiency for the stage 2 is")
+// part(c)power required to drive the compressor
+T02=T01*(pr_o1^((gamma-1)/gamma));
+P1=m*cp*(T02-T01)/n_st1;
+disp("kW",P1,"(c) power required for the 1st stage is")
+T02s=T01+(T01*(pr_o1^((gamma-1)/gamma)-1)/n_st1);
+P2=m*cp*T02s*(pr_o2^((gamma-1)/gamma)-1)/n_st2;
+disp("kW",P2,"and power required for the 2nd stage is")
+
+
+
+// part(d) air angles of the rotors and stators
+A1=%pi*d*h;
+ro_01=(p01*1e5)/(R*T01);
+cx=m/(ro_01*A1);
+    T1=T01-((cx^2)/(2*cp*1e3));
+    p1=p01*((T1/T01)^(1/((gamma-1)/gamma)));
+ro1=(p1*1e5)/(R*T1);
+cx_new=m/(ro1*A1);
+c1=cx_new;
+disp("for first stage")
+u=%pi*d*N/60;
+beta1=atand(u/c1);
+disp("degree",beta1,"beta1=")
+wst1=cp*(T02-T01)*1e3/n_st1;
+cy2=wst1/(wdf*u);
+alpha2=atand(cy2/cx_new);
+disp("degree",alpha2,"alpha2=")
+beta2=atand((u/cx_new)-tand(alpha2));
+disp("degree",beta2,"beta2=")
+R=cx_new*(tand(beta1)+tand(beta2))*100/(2*u);
+disp("%",R,"degree of reaction for the first stage is")
+
+T01_II=T02s;
+disp("for second stage")
+T02_II=T01_II*(pr_o2^((gamma-1)/gamma));
+wst2=cp*1e3*(T02_II-T01_II)/n_st2;
+alpha1s=beta2;
+cy1s=cx_new*tand(alpha1s);
+cy2s=(cy1s)+(wst2/(wdf*u));
+alpha2s=atand(cy2s/cx_new);
+disp("degree",alpha2s,"alpha2s=")
+beta1s=atand((u-cy1s)/cx_new);
+disp("degree",beta1s,"beta1s=")
+beta2s=atand((u-cy2s)/cx_new);
+disp("degree",beta2s,"beta2s=")
+R_II=cx_new*(tand(beta1s)+tand(beta2s))*100/(2*u);
+disp("%",R_II,"Degree of Reaction for the second stage is")
diff --git a/2223/CH18/EX18.26/Ex18_26.sav b/2223/CH18/EX18.26/Ex18_26.sav
new file mode 100755
index 000000000..8d52b7e96
--- /dev/null
+++ b/2223/CH18/EX18.26/Ex18_26.sav
diff --git a/2223/CH18/EX18.26/Ex18_26.sce b/2223/CH18/EX18.26/Ex18_26.sce
new file mode 100755
index 000000000..559dbb57e
--- /dev/null
+++ b/2223/CH18/EX18.26/Ex18_26.sce
@@ -0,0 +1,26 @@
+// scilab Code Exa 18.24 Calculation on an axial compressor cascade 
+
+R=0.5906; // Degree of reaction
+beta1=66;
+beta2=22;
+alpha2=61;
+p_R=0.865; // pitch-chord ratio(s/l) for rotor
+p_S=0.963; // pitch-chord ratio(s/l) for stator
+alpha_3=beta2; //  air angle at rotor and stator exit
+u=100; // test section velocity of air in m/s
+Y_D=0.077; // profile loss coefficient for stator blade row
+Y_R=0.08; // loss coefficient for rotor blade row
+beta_m=atand(0.5*(tand(beta1)+tand(beta2)));
+C_D_R=p_R*Y_R*(cosd(beta_m)^3)/(cosd(beta1)^2);
+C_L_R=(2*p_R*(tand(beta1)-tand(beta2))*cosd(beta_m))-(C_D_R*tand(beta_m));
+n_R=1-(2*C_D_R/(C_L_R*sind(2*beta_m)));
+disp("%",n_R*1e2,"the value of rotor cascade efficiency is")
+
+alpham=atand(0.5*(tand(alpha2)+tand(alpha_3)));
+C_D_S=p_S*Y_D*(cosd(alpham)^3)/(cosd(alpha2)^2);
+C_L_S=(2*p_S*(tand(alpha2)-tand(alpha_3))*cosd(alpham))-(C_D_S*tand(alpham));
+n_D=1-(2*C_D_S/(C_L_S*sind(2*alpham)));
+disp("%",n_D*1e2,"the value of diffuser cascade efficiency is")
+
+n_st=R*n_R+(1-R)*n_D;
+disp("%",n_st*1e2,"the value of stage efficiency is")
diff --git a/2223/CH18/EX18.27/Ex18_27.sav b/2223/CH18/EX18.27/Ex18_27.sav
new file mode 100755
index 000000000..d965a7217
--- /dev/null
+++ b/2223/CH18/EX18.27/Ex18_27.sav
diff --git a/2223/CH18/EX18.27/Ex18_27.sce b/2223/CH18/EX18.27/Ex18_27.sce
new file mode 100755
index 000000000..49314758b
--- /dev/null
+++ b/2223/CH18/EX18.27/Ex18_27.sce
@@ -0,0 +1,33 @@
+// scilab Code Exa 18.27 Isentropic Flow-centrifugal Air compressor 
+
+T01=335;  // in Kelvin
+p01=1.02; //  Initial Pressure in bar
+beta1=61.4; // air angle at the inlet of axial inducer blades
+gamma=1.4;
+d1=0.175; // Mean Blade ring diameter at entry
+d2=0.5; // impeller diameter at exit
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+A1=0.0412; // Area of cross section at the impeller inlet
+R=287;
+
+N(1)=5700; // rotor Speed in RPM
+N(2)=6200;
+N(3)=6700;
+N(4)=7200;
+for i=1:4
+printf("\n for N=%d rpm\n\n",N(i))
+u1=%pi*d1*N(i)/60;
+u2=%pi*d2*N(i)/60;
+c1=u1*tand(beta1);
+T1=T01-((c1^2)/(2*cp));
+p1=p01*((T1/T01)^(gamma/(gamma-1)));
+ro1=(p1*1e5)/(R*T1);
+pr0=((1+(u2^2/(cp*T01)))^(gamma/(gamma-1)));
+disp(pr0,"(a)pressure ratio is")
+m=ro1*A1*c1;
+disp("kg/s",m,"(b)mass flow rate of air is")
+T02=T01*(pr0^((gamma-1)/gamma));
+P=m*cp*(T02-T01);
+disp("kW",P*1e-3,"(c)Power required to drive the compressor P=")
+end
+
diff --git a/2223/CH18/EX18.28/Ex18_28.sav b/2223/CH18/EX18.28/Ex18_28.sav
new file mode 100755
index 000000000..586958caf
--- /dev/null
+++ b/2223/CH18/EX18.28/Ex18_28.sav
diff --git a/2223/CH18/EX18.28/Ex18_28.sce b/2223/CH18/EX18.28/Ex18_28.sce
new file mode 100755
index 000000000..5de7977fd
--- /dev/null
+++ b/2223/CH18/EX18.28/Ex18_28.sce
@@ -0,0 +1,36 @@
+// scilab Code Exa 18.28 centrifugal Air compressor 
+T01=335;  // in Kelvin
+p01=1.02; //  Initial Pressure in bar
+beta1=61.4; // air angle at the inlet of axial inducer blades
+gamma=1.4;
+N=7200; // rotor Speed in RPM
+d1=0.175; // Mean Blade ring diameter at entry
+d2=0.5; // impeller diameter at exit
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+A1=0.0412; // Area of cross section at the impeller inlet
+R=287;
+b2=A1/(%pi*d2);
+disp("cm",b2*1e2,"(a)width of the impeller at exit is")
+u2=%pi*d2*N/60; 
+//for N=7200 rpm
+p1=0.9444579; // from Ex18.27  
+pr=1.4206988; //pressure ratio 
+m=5.0061078; //mass flow rate of air in kg/s   
+T02=370.35381;
+ro2=1.1; //trial and error
+cr2(1)=m/(A1*ro2);
+n=2;
+for i=1:n
+    c2(i)=sqrt(cr2(i)^2+(u2^2));
+    T2=T02-((c2(i)^2)/(2*cp));
+    p02=pr*p01;
+    p2=p02*((T2/T02)^(1/((gamma-1)/gamma)));
+ro2=(p2*1e5)/(R*T2);
+cr2(i+1)=m/(ro2*A1);
+end
+cr=cr2(3);
+disp(p2/p1,"(b)the static pressure ratio is")
+
+//part(c)
+alpha2=atand(cr/u2);
+disp("degree",alpha2,"(c)the direction alpha2 of the absolute velocity vector(c2) or the diffuser angle at entry is")
diff --git a/2223/CH18/EX18.29/Ex18_29.sav b/2223/CH18/EX18.29/Ex18_29.sav
new file mode 100755
index 000000000..db5042d3a
--- /dev/null
+++ b/2223/CH18/EX18.29/Ex18_29.sav
diff --git a/2223/CH18/EX18.29/Ex18_29.sce b/2223/CH18/EX18.29/Ex18_29.sce
new file mode 100755
index 000000000..89f23a68d
--- /dev/null
+++ b/2223/CH18/EX18.29/Ex18_29.sce
@@ -0,0 +1,61 @@
+// scilab Code Exa 18.29 Centrifugal compressor with vaned diffuser 
+T01=310;  // in Kelvin
+p01=1.103; //  Initial Pressure in bar
+dh=0.10; // hub diameter in m
+d2=0.55; // impeller diameter in m
+c1=100; // Velocity of air at the entry of inducer
+c3=c1; // Velocity of air at diffuser exit
+shi=1.035; // power input factor
+mu=0.9; // slip factor
+m=7.5; //  in kg/s
+gamma=1.4;
+N=15e3; // rotor Speed in RPM
+disp("(a)for radially tipped blades")
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+n_tt=0.81; // total to total efficiency
+T1=T01-((c1^2)/(2*cp));
+p1=p01*((T1/T01)^(gamma/(gamma-1)));
+ro1=(p1*1e5)/(R*T1);
+A1=m/(ro1*c1);
+dt=sqrt((A1*4/(%pi))+(dh^2));
+disp("cm",dt*1e2,"(i)tip diameter of the inducer at entry is")
+d1=0.5*(dt+dh); // Mean Blade ring diameter
+u1=%pi*d1*N/60;
+w1=sqrt((u1^2)+(c1^2));
+a1=sqrt(gamma*R*T1);
+M1_rel=w1/a1;
+disp(M1_rel,"(ii)the Relative Mach number at inducer blade entry Mw1=")
+u2=%pi*d2*N/60;
+w_st=shi*mu*(u2^2);
+T02=T01+(w_st/cp);
+T02s=T01+(n_tt*(T02-T01));
+pr_0=(T02s/T01)^(gamma/(gamma-1));
+disp(pr_0,"(iii)stagnation pressure ratio developed is")
+P=m*cp*(T02-T01);
+disp("kW",P*1e-3,"(iv)the power required is")
+disp("(b)for vaned diffuser")
+c_theta2=mu*u2; // velocity of whirl(swirl component) at the impeller exit
+// vaneless space between the impeller exit and the vaned diffuser entry=0.1*impeller radius
+//r2s=r2*1.1;
+// width of the casing after the impeller exit=1.4*impeller passage width
+c_theta2s=c_theta2/(1.1*1.4);
+cr2=c1;
+cr2s=cr2/(1.1*1.4);
+c2s=sqrt((cr2s^2)+(c_theta2s^2));
+alpha2s=atand(cr2s/c_theta2s);
+disp("degree",alpha2s,"(i)the direction of flow at the diffuser entry is alpha2s=")
+T2s=T02-((c2s^2)/(2*cp));
+a2s=sqrt(gamma*R*T2s);
+M2s=c2s/a2s;
+disp(M2s,"(ii)the Mach number at the diffuser entry is")
+Ar=c2s/c3;
+d3_2s=1.16; // d3/d2s from last trial given in the book
+alpha3=acosd(cosd(alpha2s)/d3_2s);
+Ar_v=d3_2s*sind(alpha3)/(sind(alpha2s));
+disp(Ar_v,"(iii)Area ratio of the vaned diffuser is")
+T03=T02;
+T3=T03-((c3^2)/(2*cp));
+pr3_1=(((T3*T01)/(T1*T03))^(gamma/(gamma-1)))*pr_0;
+disp(pr3_1,"(iv)the static pressure ratio of the compressor is")
+disp("comment: Calculations in the book are wrong in the beginning itself for p1. so the values slightly differs here only for part(a)")
diff --git a/2223/CH18/EX18.3/Ex18_3.sav b/2223/CH18/EX18.3/Ex18_3.sav
new file mode 100755
index 000000000..cbd6af513
--- /dev/null
+++ b/2223/CH18/EX18.3/Ex18_3.sav
diff --git a/2223/CH18/EX18.3/Ex18_3.sce b/2223/CH18/EX18.3/Ex18_3.sce
new file mode 100755
index 000000000..115222ee2
--- /dev/null
+++ b/2223/CH18/EX18.3/Ex18_3.sce
@@ -0,0 +1,7 @@
+// scilab Code Exa 18.3 Irreversible flow in nozzles
+pr=0.843; // pr=p/p0
+n_n=0.95; // nozzle efficiency
+gamma=1.4;
+Ms=0.5; // from gas tables for gammma and pr value
+Ma=sqrt((2/(gamma-1))*(n_n/(1-n_n+(2/((gamma-1)*(Ms^2))))));
+disp(Ma,"actual value of the Mach number is")
diff --git a/2223/CH18/EX18.30/Ex18_30.sav b/2223/CH18/EX18.30/Ex18_30.sav
new file mode 100755
index 000000000..7c346f35a
--- /dev/null
+++ b/2223/CH18/EX18.30/Ex18_30.sav
diff --git a/2223/CH18/EX18.30/Ex18_30.sce b/2223/CH18/EX18.30/Ex18_30.sce
new file mode 100755
index 000000000..ead21177c
--- /dev/null
+++ b/2223/CH18/EX18.30/Ex18_30.sce
@@ -0,0 +1,36 @@
+// scilab Code Exa 18.30 Inward Flow Radial Gas turbine
+
+T1=873; // the gas entry temperature at nozzle in Kelvin
+p1=4; // the gas entry pressure at nozzle in bar
+n_T=0.85; // isentropic efficiency
+d2=0.4; // rotor blade ring diameter at entry in m
+d3=0.2; // rotor blade ring diameter at exit in m
+pr_t=4; // static Pressure Ratio across the turbine(p3/p1)
+pr_n=2; // static Pressure Ratio across the nozzles(p3/p1) 
+phi=0.3; // flow coefficient at impeller entry
+gamma=1.4;
+N=18e3; // rotor Speed in RPM
+m=5; // mass flow rate of gas in kg/s
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+u2=%pi*d2*N/60;
+u3=%pi*d3*N/60;
+cr2=phi*u2;
+// part(a)
+T3ss=T1/(pr_t^((gamma-1)/gamma));
+T3=T1-n_T*(T1-T3ss);
+T2s=T1/(pr_n^((gamma-1)/gamma));
+T2=T2s+(0.5*(T3-T3ss)); // half of the losses(T3-T3ss) occur in the nozzles
+p2=p1/pr_n;
+rho2=(p2*1e5)/(R*T2);
+b2=m/(rho2*cr2*%pi*d2);
+disp("cm",b2*1e2,"(a)axial width of the impeller blade passage at entry is")
+alpha2=atand(cr2/u2);
+disp("degree",alpha2,"(b)nozzle exit air angle is")
+cx3=cr2;
+beta3=atand(cx3/u3);
+disp("degree",beta3,"(c)impeller exit air angle is")
+c_theta3=0;
+c_theta2=u2;
+P=m*(u2*c_theta2-u3*c_theta3);
+disp("kW",P*1e-3,"(d)power developed is")
diff --git a/2223/CH18/EX18.31/Ex18_31.sav b/2223/CH18/EX18.31/Ex18_31.sav
new file mode 100755
index 000000000..8f5140403
--- /dev/null
+++ b/2223/CH18/EX18.31/Ex18_31.sav
diff --git a/2223/CH18/EX18.31/Ex18_31.sce b/2223/CH18/EX18.31/Ex18_31.sce
new file mode 100755
index 000000000..17d3b3c6c
--- /dev/null
+++ b/2223/CH18/EX18.31/Ex18_31.sce
@@ -0,0 +1,57 @@
+// scilab Code Exa 18.31 Cantilever Type IFR turbine
+
+P=150; // Power developed in kW
+T01=960; // the gas entry temperature at nozzle in Kelvin
+p01=3; // the gas entry pressure at nozzle in bar
+beta2=45; // air angle at rotor blade entry (from radial direction)
+beta3=65; // air angle at rotor blade exit (from radial direction)
+d2=0.2; // rotor blade ring diameter at entry in m
+d3=0.15; // rotor blade ring diameter at exit in m
+gamma=1.4;
+N=36e3; // rotor Speed in RPM
+alpha_2=15;  //  air angle at nozzle exit(from tangential direction)
+pr0=2.29; // total-to-static Pressure Ratio(p01/p3) 
+n_N=0.94; // Nozzle Efficiency 
+cp=1100; // Specific Heat at Constant Pressure in J/(kgK)
+R=cp*((gamma-1)/gamma);
+u2=%pi*d2*N/60;
+u3=%pi*d3*N/60;
+
+// part(a) mass flow rate of the gas
+cr2_theta2=tand(alpha_2); // cr2_theta2=cr2/c_theta2
+c_theta2=u2/(1-cr2_theta2); // c_theta2=cr2*tan(alpha2)+u2
+cr2=c_theta2*cr2_theta2;
+cr3=cr2;
+c_theta3=(cr3*tand(beta3))-u3;
+w_st=(u2*c_theta2)+(u3*c_theta3);
+m=P/(w_st*1e-3);
+disp("kg/s",m,"(a)mass flow rate of the gas is")
+
+// part(b)rotor blade axial length at entry
+c2=cr2/sind(alpha_2);
+T2s=T01-((0.5*(c2^2))/(cp*n_N));
+T2=T01-((T01-T2s)*n_N);
+p_rn=(T2s/T01)^(gamma/(gamma-1));
+p2=p01*p_rn;
+rho2=(p2*1e5)/(R*T2);
+b2=m/(rho2*cr2*%pi*d2);
+disp("cm",b2*1e2,"(b)rotor blade axial length at entry is")
+
+// part(c)total-to-total turbine efficiency
+T03ss=T01*(pr0^((1-gamma)/gamma));
+n_T=P/(m*cp*1e-3*(T01-T03ss));
+disp("%",n_T*1e2,"(c)total-to-total turbine efficiency is")
+
+//part(d)rotor blade length at exit
+p03=p01/pr0;
+T03=T01-(P/(m*cp*1e-3));
+c3=sqrt((cr3^2)+(c_theta3^2));
+T3=T03-((cr3^2)/(2*cp));
+p3=p03*((T3/T03)^(gamma/(gamma-1)));
+ro3=(p3*1e5)/(R*T3);
+b3=m/(ro3*cr3*%pi*d3);
+disp("cm",b3*1e2,"(d)rotor blade length at exit is")
+
+// part(e) degree of reaction
+DOR=(T2-T3)/(T01-T03);
+disp("%",DOR*1e2,"(e)degree of reaction is")
diff --git a/2223/CH18/EX18.32/Ex18_32.sav b/2223/CH18/EX18.32/Ex18_32.sav
new file mode 100755
index 000000000..782f52ecf
--- /dev/null
+++ b/2223/CH18/EX18.32/Ex18_32.sav
diff --git a/2223/CH18/EX18.32/Ex18_32.sce b/2223/CH18/EX18.32/Ex18_32.sce
new file mode 100755
index 000000000..30d6cfbdf
--- /dev/null
+++ b/2223/CH18/EX18.32/Ex18_32.sce
@@ -0,0 +1,9 @@
+// scilab Code Exa 18.32 IFR turbine stage efficiency
+
+// part(b)
+R=0.48;
+sigma_s=0.6;
+n_n=0.92;
+alpha_2=15;  //  air angle at nozzle exit(from tangential direction)
+n_st=2*sigma_s*sqrt(n_n*(1-R))*cosd(alpha_2);
+disp("%",n_st*100,"stage efficiency of the radial turbine is")
diff --git a/2223/CH18/EX18.33/Ex18_33.sav b/2223/CH18/EX18.33/Ex18_33.sav
new file mode 100755
index 000000000..fd6d6ad6f
--- /dev/null
+++ b/2223/CH18/EX18.33/Ex18_33.sav
diff --git a/2223/CH18/EX18.33/Ex18_33.sce b/2223/CH18/EX18.33/Ex18_33.sce
new file mode 100755
index 000000000..37419ad21
--- /dev/null
+++ b/2223/CH18/EX18.33/Ex18_33.sce
@@ -0,0 +1,35 @@
+// scilab Code Exa 18.33 Vertical Axis Crossflow Wind turbine
+
+c1=24/3.6; // wind speed in m/s
+c2=30/3.6; // rotor speed in m/s
+m1=25; // mass flow rate of air at wind side in kg/s
+m2=31.25; // rotor  air mass flow rate in kg/s
+d1=3; // rotor outer diameter in m
+d2=2; // rotor inner diameter in m
+gamma=1.4;
+alpha=37;  //  air angle at rotor entry(from tangential direction)
+c(1)=c1;
+c(2)=c2;
+m(1)=m1;
+m(2)=m2;
+
+for i=1:2
+c_theta1=c(i)*cosd(alpha);
+u1=c_theta1/2;
+u2=u1*d2/d1;
+disp("kmph",c(i)*3.6,"for speed=")
+
+// part(a)optimum rotor speed
+N=60*u1/(%pi*d1);
+disp("rpm",N,"(a)optimum rotor speed is")
+
+// part(b)blade to wind speed ratio
+sigma=u1/c(i);
+disp(sigma,"blade to wind speed ratio is")
+
+// part(c)hydraulic powers and efficiencies
+Ph=m(i)*((2*(u1^2))+(u2^2));
+disp("Watts",Ph,"(c)hydraulic power is")
+n_h=((2*(u1^2))+(u2^2))/(0.5*(c(i)^2));
+disp("%",n_h*1e2,"and hydraulic efficiency is")
+end
diff --git a/2223/CH18/EX18.34/Ex18_34.sav b/2223/CH18/EX18.34/Ex18_34.sav
new file mode 100755
index 000000000..7315d0f27
--- /dev/null
+++ b/2223/CH18/EX18.34/Ex18_34.sav
diff --git a/2223/CH18/EX18.34/Ex18_34.sce b/2223/CH18/EX18.34/Ex18_34.sce
new file mode 100755
index 000000000..6672f1185
--- /dev/null
+++ b/2223/CH18/EX18.34/Ex18_34.sce
@@ -0,0 +1,16 @@
+// scilab Code Exa 18.34 Counter Rotating fan
+
+n=0.809; // combined efficiency of the fans
+phi=0.245; // flow coefficient
+A=0.212; // data from Ex14.1
+d=0.45; // data from Ex14.1
+u=22.62; // data from Ex14.1
+cx=phi*u;
+Q=1.175; // in m3/s
+delp0_I=550.755; // data from Ex14.1
+delp0_II=delp0_I;
+delp0=delp0_I+delp0_II;
+disp("mm W.G.",delp0/9.81,"(a)the overall pressure rise obtained is")
+IP=Q*delp0; // power required for isentropic flow in Watts
+P=IP/n;
+disp("kW",P*1e-3,"(b)the Power required is")
diff --git a/2223/CH18/EX18.35/Ex18_35.sav b/2223/CH18/EX18.35/Ex18_35.sav
new file mode 100755
index 000000000..896094380
--- /dev/null
+++ b/2223/CH18/EX18.35/Ex18_35.sav
diff --git a/2223/CH18/EX18.35/Ex18_35.sce b/2223/CH18/EX18.35/Ex18_35.sce
new file mode 100755
index 000000000..b19955a2f
--- /dev/null
+++ b/2223/CH18/EX18.35/Ex18_35.sce
@@ -0,0 +1,26 @@
+// scilab Code Exa 18.35 Sirocco Radial fan 1440 rpm
+
+d2=0.4; // outer diameter of the impeller in m
+d1=0.36; // inner diameter of the impeller in m
+b=0.5; // axial length of the impeller in m
+rho=1.25; // density of air in kg/m3
+N=1440; // rotor Speed in RPM
+P=50; // Power required in kW
+
+u1=%pi*d1*N/60;
+u2=%pi*d2*N/60;
+ 
+beta1=atand(d2/d1);
+disp("degree",beta1,"(a)the blade air angle at the impeller entry beta1=")
+beta2=90-beta1;
+disp("degree",beta2,"and the blade air angle at the impeller exit beta2=")
+delp0=2*rho*(u2^2);
+disp("mm W.G.",delp0/9.81,"(b)the stagnation pressure rise across the fan is") 
+cr1=u1*tand(beta1);
+m=rho*cr1*%pi*d1*b;
+disp("kg/s",m,"(c)mass flow rate of the air through the fan is")
+c_theta1=0; // for zero inlet swirl
+w_st=2*(u2^2);
+IP=m*w_st/1000; // ideal power required to drive the fan in kW
+n=IP/P;
+disp("%",n*1e2,"(d)the Efficiency of the fan is") 
diff --git a/2223/CH18/EX18.37/Ex18_37.sav b/2223/CH18/EX18.37/Ex18_37.sav
new file mode 100755
index 000000000..289e95f40
--- /dev/null
+++ b/2223/CH18/EX18.37/Ex18_37.sav
diff --git a/2223/CH18/EX18.37/Ex18_37.sce b/2223/CH18/EX18.37/Ex18_37.sce
new file mode 100755
index 000000000..2a1b25908
--- /dev/null
+++ b/2223/CH18/EX18.37/Ex18_37.sce
@@ -0,0 +1,52 @@
+// scilab Code Exa 18.37 Calculation for the specific speed
+
+//part(1)specific speed of Axial flow gas turbine
+P1=0.5e3; // Gas Turbine Power Output in kW
+N1=60; // Speed in RPS
+omega1=%pi*2*N1;
+ro1=2;
+delh_1=30; // change of enthalpy in kJ
+NS_1=omega1*sqrt(P1*10e2/ro1)*((delh_1*1e3)^(-5/4));
+disp(NS_1,"1.the specific speed of Axial flow gas turbine is")
+
+//part(2)specific speed of IFR gas turbine
+P2=0.75e3; // Gas Turbine Power Output in kW
+N2=300; // Speed in RPS
+omega2=%pi*2*N2;
+ro2=1;
+delh_2=250; // change of enthalpy in kJ
+NS_2=omega2*sqrt(P2*10e2/ro2)*((delh_2*1e3)^(-5/4));
+disp(NS_2,"2.the specific speed of IFR gas turbine is") 
+
+// part(3)the specific speed of an axial compressor
+N_c=120; // Speed in RPS
+omega_c=%pi*2*N_c;
+Q_c=25; // flow rate in m3/s
+delh_3=40; // change of enthalpy in kJ
+NS_c=omega_c*sqrt(Q_c)*((delh_3*1e3)^(-3/4));
+disp(NS_c,"3.the specific speed of an axial compressor is")
+
+// part(4)the specific speed of a centrifugal compressor
+Q=5; // flow rate in m3/s
+delh_4=35; // change of enthalpy in kJ
+NS_4=omega_c*sqrt(Q)*((delh_4*1e3)^(-3/4));
+disp(NS_4,"4.the specific speed of a centrifugal compressor is")
+
+// part(5)the specific speed of an axial fan
+N5=22; // Speed in RPS
+omega_5=2*%pi*N5;
+Q_5=3.5; // flow rate in m3/s
+rho=1.25; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+H1=55/rho; // head in m
+NS_5=omega_5*sqrt(Q_5)*((g*H1)^(-3/4));
+disp(NS_5,"5.the dimensionless specific speed of an axial fan is")
+
+// part(6)the specific speed of a Radial fan
+N6=20; // Speed in RPS
+omega_6=2*%pi*N6;
+Q_6=1.4; // flow rate in m3/s
+
+H2=52/rho; // head in m
+NS_6=omega_6*sqrt(Q_6)*((g*H2)^(-3/4));
+disp(NS_6,"6.the dimensionless specific speed of a Radial fan is")
diff --git a/2223/CH18/EX18.38/Ex18_38.sav b/2223/CH18/EX18.38/Ex18_38.sav
new file mode 100755
index 000000000..9997f8ac9
--- /dev/null
+++ b/2223/CH18/EX18.38/Ex18_38.sav
diff --git a/2223/CH18/EX18.38/Ex18_38.sce b/2223/CH18/EX18.38/Ex18_38.sce
new file mode 100755
index 000000000..dc4a3785f
--- /dev/null
+++ b/2223/CH18/EX18.38/Ex18_38.sce
@@ -0,0 +1,28 @@
+// scilab Code Exa 18.38 Kaplan turbine 70 rpm
+
+//part(a)flow rate and specific speed 
+P=8e3; // Gas Power Output in kW
+N=70; // Speed in RPM
+H=10; // net head in m
+n_m=0.85; // efficiency
+omega=%pi*2*N/60;
+NS=omega*sqrt(P*10e2)*(H^(-5/4))/549.016;
+disp(NS,"(a)the specific speed of turbine is")
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+Q=P*1e3/(n_m*rho*g*H);
+disp("m3/s",Q,"and the flow rate is")
+
+// part(b) determining the speed, flow rate and power for the model
+Dp_m=12; // Dp_m=Dp/Dm
+Np=N; // Speed for prototype
+Hm=3; // head of the model
+Hp=H; // head for prototype
+Nm=Np*Dp_m*sqrt(Hm/Hp);
+disp("rpm",Nm,"(b)speed for the model is")
+Dm_p=1/Dp_m;
+Qp=Q;
+Qm=(Dm_p^2)*sqrt(Hm/Hp)*Qp;
+disp("m3/s",Qm,"the flow rate for model is")
+Pm=n_m*rho*g*Qm*Hm;
+disp("kW",Pm*1e-3,"the power for the model is")
diff --git a/2223/CH18/EX18.39/Ex18_39.sav b/2223/CH18/EX18.39/Ex18_39.sav
new file mode 100755
index 000000000..4b7b7c075
--- /dev/null
+++ b/2223/CH18/EX18.39/Ex18_39.sav
diff --git a/2223/CH18/EX18.39/Ex18_39.sce b/2223/CH18/EX18.39/Ex18_39.sce
new file mode 100755
index 000000000..d34382130
--- /dev/null
+++ b/2223/CH18/EX18.39/Ex18_39.sce
@@ -0,0 +1,22 @@
+// scilab Code Exa 18.39 Calculation for the Pelton Wheel
+
+Nm=102; // Speed for the model in RPM
+Hm=30; // net head for the model in m
+n_m=1; // Assuming efficiency
+Qm=0.345; // discharge in m3/s
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+omega_m=%pi*2*Nm/60;
+Pm=n_m*rho*g*Qm*Hm;
+NS=omega_m*sqrt(Pm)*(Hm^(-5/4))/549.016;
+disp(NS,"the specific speed of turbine is")
+
+// determining the speed, flow rate and power for the prototype
+Hp=1500; // head for prototype
+Pp=((Hp/Hm)^(3/2))*Pm;
+disp("MW",Pp*1e-6,"the power for the prototype is")
+omega_p=NS*549.016*(Hp^(5/4))/(sqrt(Pp));
+Np=omega_p*60/(2*%pi);
+disp("rpm",Np,"speed for the prototype is")
+Qp=sqrt(Hp/Hm)*Qm;
+disp("m3/s",Qp,"the flow rate for prototype is")
diff --git a/2223/CH18/EX18.4/Ex18_4.sav b/2223/CH18/EX18.4/Ex18_4.sav
new file mode 100755
index 000000000..e69b02c51
--- /dev/null
+++ b/2223/CH18/EX18.4/Ex18_4.sav
diff --git a/2223/CH18/EX18.4/Ex18_4.sce b/2223/CH18/EX18.4/Ex18_4.sce
new file mode 100755
index 000000000..8e55e700d
--- /dev/null
+++ b/2223/CH18/EX18.4/Ex18_4.sce
@@ -0,0 +1,29 @@
+// scilab Code Exa 18.4 Calculation on a Diffuser 
+
+pe=35; // Initial Pressure in mm W.G.
+pa=1.0135; // ambient pressure in bar
+c1=100; // entry velocity in m/s
+C_pa=0.602; // actual pressure recovery coefficient
+ro=1.25; // density in kg/m3
+g=9.81; // Gravitational acceleration in m/s^2
+Ar=1.85; // Area Ratio of Diffuser
+
+// part(a)
+C_ps=1-(1/(Ar^2));
+disp(C_ps,"(a)ideal value of the pressure recovery coefficient is")
+
+// part(b)
+n_D=C_pa/C_ps;
+disp ("%",n_D*1e2,"(b)Efficiency of the diffuser is")
+
+// part(c)
+p1=pa+(pe*g*1e-5);
+p01=p1+(0.5*ro*(c1^2)*1e-5);
+delp_0=(C_ps-C_pa)*(0.5*ro*(c1^2)*1e-5);
+disp("mm W.G.",delp_0*1e5/g,"(c)the stagnation pressure loss across the diffuser is")
+
+// part(d)
+p02=p01-delp_0;
+c2=c1/Ar;
+p2=p02-(0.5*ro*(c2^2)*1e-5);
+disp("mm W.G.",(p2-pa)*1e5/g,"(d)the gauge pressure at the diffuser exit is")
diff --git a/2223/CH18/EX18.40/Ex18_40.sav b/2223/CH18/EX18.40/Ex18_40.sav
new file mode 100755
index 000000000..3b98354f1
--- /dev/null
+++ b/2223/CH18/EX18.40/Ex18_40.sav
diff --git a/2223/CH18/EX18.40/Ex18_40.sce b/2223/CH18/EX18.40/Ex18_40.sce
new file mode 100755
index 000000000..bf1ff16a8
--- /dev/null
+++ b/2223/CH18/EX18.40/Ex18_40.sce
@@ -0,0 +1,27 @@
+// scilab Code Exa 18.40 Calculation for the Francis turbine
+
+// part(a) determining the speed, specific speed and power for the model
+Qm=0.148; // discharge in m3/s
+N=910; // Speed in RPM
+Hm=25; // net head in m
+n=0.9; // efficiency
+omega=%pi*2*N/60;
+NS=omega*sqrt(Qm)*(Hm^(-3/4))*0.1804;
+disp(NS,"(a)the specific speed of turbine is")
+Nu=N/(sqrt(Hm));
+disp("rpm",Nu,"unit speed for the model is")
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+Pm=rho*g*Qm*Hm;
+disp("kW",Pm*1e-3,"the power for the model is")
+
+// part(b)determining the speed, flow rate and power for the prototype
+Hp=250; // head for prototype
+Dp_m=6; // Dp_m=Dp/Dm
+Qp=sqrt(Hp/Hm)*Qm*(Dp_m^2);
+disp("m3/s",Qp,"(b)the flow rate for prototype is")
+Pp=rho*g*Qp*Hp*n;
+disp("MW",Pp*1e-6,"the power for the prototype is")
+omega_p=NS*(Hp^(3/4))/(0.1804*sqrt(Qp));
+Np=omega_p*60/(2*%pi);
+disp("rpm",Np,"speed for the prototype is")
diff --git a/2223/CH18/EX18.41/Ex18_41.sav b/2223/CH18/EX18.41/Ex18_41.sav
new file mode 100755
index 000000000..d2bd3875e
--- /dev/null
+++ b/2223/CH18/EX18.41/Ex18_41.sav
diff --git a/2223/CH18/EX18.41/Ex18_41.sce b/2223/CH18/EX18.41/Ex18_41.sce
new file mode 100755
index 000000000..adbe3a3c5
--- /dev/null
+++ b/2223/CH18/EX18.41/Ex18_41.sce
@@ -0,0 +1,19 @@
+// scilab Code Exa 18.41 Calculation for the Pelton Wheel
+NS=0.1; //specific speed
+H1=1000; // net head for the model in m
+Q1=1; // discharge in m3/s
+omega1=NS*(H1^(3/4))/(sqrt(Q1)*0.1804);
+N1=omega1*60/(2*%pi);
+disp("rpm",N1,"speed of the rotation is")
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+P1=rho*g*Q1*H1;
+
+// determining the speed, flow rate and power for the prototype
+H2=100; // head for prototype
+N2=N1*sqrt(H2/H1);
+disp("rpm",N2,"speed for the prototype is")
+Q2=sqrt(H2/H1)*Q1;
+disp("m3/s",Q2,"the discharge for the prototype is")
+P2=((H2/H1)^(3/2))*P1;
+disp("MW",P2*1e-6,"the power for the prototype is")
diff --git a/2223/CH18/EX18.42/Ex18_42.sav b/2223/CH18/EX18.42/Ex18_42.sav
new file mode 100755
index 000000000..6a9c549e8
--- /dev/null
+++ b/2223/CH18/EX18.42/Ex18_42.sav
diff --git a/2223/CH18/EX18.42/Ex18_42.sce b/2223/CH18/EX18.42/Ex18_42.sce
new file mode 100755
index 000000000..5d8442489
--- /dev/null
+++ b/2223/CH18/EX18.42/Ex18_42.sce
@@ -0,0 +1,23 @@
+// scilab Code Exa 18.42 Calculation for Tidal Power Plant
+
+T=50e6; // capacity of basin in cubic meters of sea water
+N=60; // Speed for the model in RPM
+NS=3; //specific speed
+H=9.8; // net head for the model in m
+n_o=0.78; // Assuming efficiency
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+n(1)=5; // number of turbines
+n(2)=10;
+omega=%pi*2*N/60;
+
+P=(NS^2)*(H^(5/2))*(549.016^2)/(omega^2);
+disp("MW",P*1e-6,"(a)the power for the turbines is")
+Q=P/(n_o*rho*g*H);  // discharge in m3/s
+disp("m3/s",Q,"(b)the discharge rate for the turbines is")
+disp("(c)")
+for i=1:2
+    disp(n(i),"when number of turbines are:")
+    t=T/(n(i)*Q*3600);
+disp("hours",t,"duration of operation is")
+end
diff --git a/2223/CH18/EX18.43/Ex18_43.sav b/2223/CH18/EX18.43/Ex18_43.sav
new file mode 100755
index 000000000..142b5db00
--- /dev/null
+++ b/2223/CH18/EX18.43/Ex18_43.sav
diff --git a/2223/CH18/EX18.43/Ex18_43.sce b/2223/CH18/EX18.43/Ex18_43.sce
new file mode 100755
index 000000000..6d1a279dc
--- /dev/null
+++ b/2223/CH18/EX18.43/Ex18_43.sce
@@ -0,0 +1,37 @@
+// scilab Code Exa 18.43 Francis turbine 250 rpm
+
+NS=0.4; //specific speed
+N=250; // Speed in RPM
+H=75; // net head in m
+beta3=25; // exit angle of the runner blades
+n_o=0.81; // overall efficiency
+g=9.81; // gravitational acceleration in m/s2
+rho=1000; // density in kg/m3
+// part(a)
+u2=0.6*sqrt(2*g*H);
+cr2=0.21*sqrt(2*g*H);
+omega=%pi*2*N/60;
+Q=(NS^2)*(H^(3/2))/((0.1804^2)*(omega^2));
+disp("m3/s",Q,"(a)the discharge rate for the turbine is")
+// part(b)
+d2=u2*60/(%pi*N);
+disp("m",d2,"(b)outer diameter of the runner blade ring is")
+cr3=cr2;
+cx3=cr3;
+//Euler work,w_ET=u2*c_theta2
+c_theta2=((g*H)-(0.5*(cx3^2)))/u2;
+u3=cx3/(tand(beta3));
+d3=u3*60/(%pi*N);
+disp("m",d3,"and inner diameter of the runner blade ring is")
+// part(c)
+alpha2=atand(cr2/c_theta2);
+disp("degree",alpha2,"(c)the inlet guide vane exit angle is")
+beta2=atand(cr2/(c_theta2-u2));
+disp("degree",beta2,"and inlet angle of the runner blades is beta2= ")
+// part(d)
+n_h=(u2*c_theta2)/(g*H);
+disp("%",n_h*1e2,"(d)the hydraulic efficiency is")
+// part(e)
+P=n_o*rho*g*Q*H;
+disp("MW",P*1e-6,"(e)the output power is")
+disp("comment: the calculation for c_theta2 is done wrongly in the book. hence the values of alpha2,beta2, n_h differs from the book.")
diff --git a/2223/CH18/EX18.44/Ex18_44.sav b/2223/CH18/EX18.44/Ex18_44.sav
new file mode 100755
index 000000000..9b645247a
--- /dev/null
+++ b/2223/CH18/EX18.44/Ex18_44.sav
diff --git a/2223/CH18/EX18.44/Ex18_44.sce b/2223/CH18/EX18.44/Ex18_44.sce
new file mode 100755
index 000000000..d04a95324
--- /dev/null
+++ b/2223/CH18/EX18.44/Ex18_44.sce
@@ -0,0 +1,43 @@
+// scilab Code Exa 18.44 Pelton Wheel 360 rpm
+
+d=2; // mean diameter in m
+N=360; // Speed in RPM
+theta=150; //deflection angle of water jet in degree
+H=140; // net head for the model in m
+q=45000; // discharge in litres/min
+Q=q*1e-3/60; // in m3/s
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+// part(a)
+u=%pi*d*N/60;
+c2=sqrt(2*g*H);
+sigma=u/c2;
+disp(sigma,"(a)blade to jet speed ratio is")
+// part(b)
+w2=c2-u;
+w3=w2;
+beta2=0;
+beta3=180-theta;
+cy2=c2;
+cy3=u-(w3*cosd(beta3));
+w_T=u*(cy2-cy3);
+m=rho*Q;
+P_T=m*w_T;
+disp("kW",P_T*1e-3,"(b)the power developed is")
+// part(c)
+n=w_T/(0.5*(c2^2));
+disp("%",n*1e2,"(c)the efficiency is")
+// part(d)
+n_max=0.5*(1+cosd(beta3));
+disp("%",n_max*1e2,"(d)the Maximum efficiency is")
+P_max=m*g*H*n_max;
+disp("kW",P_max*1e-3,"and the Maximum power developed is")
+// part(e)
+sigma_opt=0.5; // for Maximum efficiency
+u_opt=sigma_opt*c2;
+N_opt=u_opt*60/(d*%pi);
+disp("rpm",N_opt,"(e)speed of the rotation corresponding to Maximum efficiency is")
+// part(f)
+omega=%pi*2*N/60;
+NS=omega*sqrt(P_T)*(H^(-5/4))/549.016;
+disp(NS,"(f)the specific speed of turbine is")
diff --git a/2223/CH18/EX18.45/Ex18_45.sav b/2223/CH18/EX18.45/Ex18_45.sav
new file mode 100755
index 000000000..b1ddd766e
--- /dev/null
+++ b/2223/CH18/EX18.45/Ex18_45.sav
diff --git a/2223/CH18/EX18.45/Ex18_45.sce b/2223/CH18/EX18.45/Ex18_45.sce
new file mode 100755
index 000000000..972ae329d
--- /dev/null
+++ b/2223/CH18/EX18.45/Ex18_45.sce
@@ -0,0 +1,32 @@
+// scilab Code Exa 18.45 Kaplan turbine 120 rpm
+
+N=120; // Speed in RPM
+H=25; // net head in m
+Q=120; // discharge in m3/s
+dt=5; // runner diameter in m
+dh_t=0.4; // hub-tip ratio of the runner
+beta2=150; //inlet angle of the runner blades in degree
+n_o=0.8; // overall efficiency
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+// part(a)
+P=n_o*rho*g*Q*H;
+disp("MW",P*1e-6,"(a)the output power is")
+// part(b)
+omega=%pi*2*N/60;
+NS=omega*sqrt(P)*(H^(-5/4))/549.016;
+disp(NS,"(b)the specific speed of turbine is")
+// part(c)
+dh=dh_t*dt;
+d=0.5*(dt+dh); // mean diameter of the impeller blade in m
+u=%pi*d*N/60;
+cx=Q*4/(%pi*(dt^2-dh^2));
+cy2=u-(cx*tand(90-(180-beta2)));
+alpha2=atand(cx/cy2);
+disp("degree",alpha2,"(c)the inlet guide vane exit angle is")
+// part(d)
+beta3=atand(cx/u);
+disp("degree",beta3,"(d)the exit angle of the runner blades is beta3= ")
+// part(e)
+n_h=(u*cy2)/(g*H);
+disp("%",n_h*1e2,"(e)the hydraulic efficiency is")
diff --git a/2223/CH18/EX18.46/Ex18_46.sav b/2223/CH18/EX18.46/Ex18_46.sav
new file mode 100755
index 000000000..b60ee9f6a
--- /dev/null
+++ b/2223/CH18/EX18.46/Ex18_46.sav
diff --git a/2223/CH18/EX18.46/Ex18_46.sce b/2223/CH18/EX18.46/Ex18_46.sce
new file mode 100755
index 000000000..b23c1e020
--- /dev/null
+++ b/2223/CH18/EX18.46/Ex18_46.sce
@@ -0,0 +1,34 @@
+// scilab Code Exa 18.46 Fourneyron Turbine 360 rpm
+
+d2=3; // outer diameter of the impeller in m
+d1=1.5; // inner diameter of the impeller in m
+H=50; // net head in m
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+N=360; // rotor Speed in RPM
+n_o=0.785; // overall efficiency
+P=4; // Power Output in MW
+u1=%pi*d1*N/60;
+u2=%pi*d2*N/60;
+// part(a)
+Q=P*1e6/(n_o*rho*g*H);
+disp("m3/s",Q,"(a)the discharge is")
+c2=9; // velocity of water at exit in m/s
+// part(b)
+w_ET=(g*H)-(0.5*(c2^2));
+n_h=w_ET/(g*H);
+disp("%",n_h*1e2,"(b)the hydraulic efficiency is")
+// part(c)
+cr2=c2;
+b=Q/(cr2*%pi*d2); // axial length of the impeller in m
+disp("cm",b*1e2,"(c)the runner passage width is")
+// part(d)
+beta2=atand(cr2/u2);
+disp("degree",beta2,"(d) the blade air angle at the impeller exit beta2=")
+c_theta1=w_ET/u1;
+cr1=Q/(b*%pi*d1);
+beta1=atand(cr1/(u1-c_theta1));
+disp("degree",beta1,"and the blade air angle at the impeller entry beta1=")
+// part(e)
+alpha1=atand(cr1/c_theta1);
+disp("degree",alpha1,"(e)the guide vane exit angle is")
diff --git a/2223/CH18/EX18.47/Ex18_47.sav b/2223/CH18/EX18.47/Ex18_47.sav
new file mode 100755
index 000000000..5f5e27c3a
--- /dev/null
+++ b/2223/CH18/EX18.47/Ex18_47.sav
diff --git a/2223/CH18/EX18.47/Ex18_47.sce b/2223/CH18/EX18.47/Ex18_47.sce
new file mode 100755
index 000000000..853707b83
--- /dev/null
+++ b/2223/CH18/EX18.47/Ex18_47.sce
@@ -0,0 +1,38 @@
+// scilab Code Exa 18.47 Crossflow Radial Hydro turbine
+
+N=50; // Speed in RPM
+H=25; // net head in m
+Q=150; // discharge in m3/s
+P=20; // Power Output in MW
+d1=3.5; //  runner diameter in m
+dr=1.3; // diameter ratio of the runner
+rho=1000; // density in kg/m3
+g=9.81; // gravitational acceleration in m/s2
+u1=%pi*d1*N/60;
+u2=u1/dr;
+c_theta1=2*u1;
+c_theta2=u2;
+w_st1=(u1*c_theta1)-(u2*c_theta2);
+u3=u2;
+c_theta3=u2;
+c_theta4=0;
+w_st2=(u3*c_theta3)-(u1*c_theta4);
+w_st=w_st1+w_st2;
+// part(a)
+n_h=w_st/(g*H);
+disp("%",n_h*1e2,"(a)the hydraulic efficiency is")
+Ph=rho*Q*w_st;
+disp("MW",Ph*1e-6,"and the hydraulic power is")
+n_o=P*1e6/(rho*Q*g*H);
+disp("%",n_o*1e2,"and the overall efficiency is")
+// part(b)
+omega=%pi*2*N/60;
+NS=omega*sqrt(P*1e6)*(H^(-5/4))/549.016;
+disp(NS,"(b)the specific speed of turbine is")
+// part(c)
+disp("(c)Adopting the flow model of the crossflow wind turbine")
+P_h=rho*Q*((2*(u1^2))+(u2^2));
+disp("MW",P_h*1e-6,"the hydraulic power is")
+nh=((2*(u1^2))+(u2^2))/(g*H);
+disp("%",nh*1e2,"and hydraulic efficiency is")
+
diff --git a/2223/CH18/EX18.48/Ex18_48.sav b/2223/CH18/EX18.48/Ex18_48.sav
new file mode 100755
index 000000000..e26068996
--- /dev/null
+++ b/2223/CH18/EX18.48/Ex18_48.sav
diff --git a/2223/CH18/EX18.48/Ex18_48.sce b/2223/CH18/EX18.48/Ex18_48.sce
new file mode 100755
index 000000000..c92769738
--- /dev/null
+++ b/2223/CH18/EX18.48/Ex18_48.sce
@@ -0,0 +1,13 @@
+// scilab Code Exa 18.48 Calculation on a Draft Tube 
+
+pa=1.013; // atmospheric pressure in bar
+p3=0.4*pa; // turbine exit pressure in bar
+rho=1e3; // density in kg/m3
+g=9.81; // Gravitational acceleration in m/s^2
+n_D=0.82; // Efficiency of the Draft Tube
+delHi=3.1058869; // from Ex 18.5
+// part(b)
+Hd=delHi;
+Hs=((pa-p3)*1e5/(rho*g))-(n_D*Hd); // Hs=Z3-Z4
+disp("m",Hs,"(b)the suction head(height of the turbine exit above the tail race) is")
+disp("comment: the calculation for Hs is done wrongly in the book. hence the value of Hs differs from the book.")
diff --git a/2223/CH18/EX18.49/Ex18_49.sav b/2223/CH18/EX18.49/Ex18_49.sav
new file mode 100755
index 000000000..252377f3e
--- /dev/null
+++ b/2223/CH18/EX18.49/Ex18_49.sav
diff --git a/2223/CH18/EX18.49/Ex18_49.sce b/2223/CH18/EX18.49/Ex18_49.sce
new file mode 100755
index 000000000..002551e2f
--- /dev/null
+++ b/2223/CH18/EX18.49/Ex18_49.sce
@@ -0,0 +1,34 @@
+// scilab Code Exa 18.49 Centrifugal pump 890 kW
+
+H=50; // head developed in m
+P=890; // Power required in kW
+NS=0.75; //specific speed
+rho=1e3;
+g=9.81; // Gravitational acceleration in m/s^2
+n_h=0.91; // hydraulic efficiency
+f=0.925; // blockage factor for the flow
+Q=1.5; // discharge in m3/s of water
+u2=0.8*sqrt(2*g*H);
+cr2=0.3*sqrt(2*g*H);
+dr=0.5; // diameter ratio(d1/d2)
+// part(a)
+omega=NS*(H^(3/4))/(0.1804*sqrt(Q));
+N=omega*60/(2*%pi);
+disp("rpm",N,"(a)the speed of rotation is")
+// part(b) impeller diameter
+d2=u2*60/(%pi*N);
+disp("m",d2,"(b)the impeller diameter is")
+//part(c)
+c_theta2=g*H/(u2*n_h);
+beta2=atand(cr2/(u2-c_theta2));
+disp("degree",beta2,"(c)the blade air angle at the impeller exit beta2=")
+u1=u2*dr;
+cr1=cr2;
+beta1=atand(cr1/u1);
+disp("degree",beta1,"and the blade air angle at the impeller entry beta1=")
+//part(d)
+b2=Q/(cr2*%pi*d2*f);
+disp("m",b2,"(d)the impeller width at exit is")
+//part(e)overall Efficiency
+n_o=rho*Q*H*g/(P*1e3);
+disp("%",n_o*1e2,"(e)overall efficiency is")
diff --git a/2223/CH18/EX18.5/Ex18_5.sav b/2223/CH18/EX18.5/Ex18_5.sav
new file mode 100755
index 000000000..b7a81337b
--- /dev/null
+++ b/2223/CH18/EX18.5/Ex18_5.sav
diff --git a/2223/CH18/EX18.5/Ex18_5.sce b/2223/CH18/EX18.5/Ex18_5.sce
new file mode 100755
index 000000000..2b130aef7
--- /dev/null
+++ b/2223/CH18/EX18.5/Ex18_5.sce
@@ -0,0 +1,30 @@
+// scilab Code Exa 18.5 Calculation on a Draft Tube 
+
+c2=6.25; // exit velocity in m/s
+ro=1e3; // density in kg/m3
+g=9.81; // Gravitational acceleration in m/s^2
+AR=1.6; // Area Ratio of Diffuser
+Q=100; // discharge in m3/s
+n_D=0.82; // Efficiency of the Draft Tube
+
+// part(a)
+c1=c2*AR;
+A1=Q/c1;
+disp("m2",A1,"(a)area of cross-section at entry is")
+A2=A1*AR;
+disp("m2",A2,"and the area of cross-section at exit is")
+
+// part(b)
+delHi=((c1^2)-(c2^2))/(2*g);
+delH_a=delHi*n_D;
+disp("m",delH_a,"(b)actual head gained by the Draft Tube is")
+
+// part(c)
+m=ro*Q;
+delP_a=m*g*delH_a;
+disp("MW",delP_a*1e-6,"(c)the additional power generated is")
+
+// part(d)
+Loss=delHi-delH_a;
+disp("m",Loss,"(d)the loss of head due to losses in the draft tube is")
+
diff --git a/2223/CH18/EX18.50/Ex18_50.sav b/2223/CH18/EX18.50/Ex18_50.sav
new file mode 100755
index 000000000..c2667951a
--- /dev/null
+++ b/2223/CH18/EX18.50/Ex18_50.sav
diff --git a/2223/CH18/EX18.50/Ex18_50.sce b/2223/CH18/EX18.50/Ex18_50.sce
new file mode 100755
index 000000000..fbcd99022
--- /dev/null
+++ b/2223/CH18/EX18.50/Ex18_50.sce
@@ -0,0 +1,27 @@
+// scilab Code Exa 18.50 Centrifugal pump 1500 rpm
+
+N=1500; // rotor Speed in RPM
+H=5.2; // head in m
+b=2/100; // width in m
+d1=2.5/100; // entry diameter of the blade ring in m
+d2=0.1; // exit diameter of the blade ring in m
+rho=1e3;
+g=9.81; // Gravitational acceleration in m/s^2
+n_o=0.75; // overall Efficiency of the drive
+u2=%pi*d2*N/60;
+u1=u2*d1/d2;
+// part(a)impeller blade angle at the entry
+c_r2=0.4*u2;
+c_r1=c_r2*d2/d1;
+beta1=atand(c_r1/u1);
+disp("degree",beta1,"(a)the impeller blade angle at the entry beta1=")
+//part(b) discharge
+Q=c_r1*%pi*d1*b;
+disp("litres/sec",Q*1e3,"(b)the discharge is")
+//part(c)Power required
+P=(rho*Q*g*H)/(n_o);
+disp("kW",P*1e-3,"(a)Power required to drive the pump is")
+// part(d)
+omega=%pi*2*N/60;
+NS=(H^(-3/4))*0.1804*(omega)*sqrt(Q);
+disp(NS,"(d)the specific speed is")
diff --git a/2223/CH18/EX18.51/Ex18_51.sav b/2223/CH18/EX18.51/Ex18_51.sav
new file mode 100755
index 000000000..4b0bf83cb
--- /dev/null
+++ b/2223/CH18/EX18.51/Ex18_51.sav
diff --git a/2223/CH18/EX18.51/Ex18_51.sce b/2223/CH18/EX18.51/Ex18_51.sce
new file mode 100755
index 000000000..eb25b0c62
--- /dev/null
+++ b/2223/CH18/EX18.51/Ex18_51.sce
@@ -0,0 +1,30 @@
+// scilab Code Exa 18.51 Axial pump 360 rpm
+
+N=360; // rotor Speed in RPM
+dh=0.30; // hub diameter of the impeller in m
+beta2=48; // exit angle of the runner blades(from the tangential direction)
+cx=5; // axial velocity of water through the impeller in m/s
+n_h=0.87; // hydraulic efficiency
+n_o=0.83; // overall Efficiency 
+Q=2.5; // discharge in m3/s
+rho=1e3;
+g=9.81; // Gravitational acceleration in m/s^2
+//part(a)
+dt=sqrt((4*Q/(cx*%pi))+(dh^2));
+disp("m",dt,"(a)the impeller tip diameter is")
+// part(b)impeller blade angle at the entry
+d=0.5*(dt+dh); // mean diameter of the impeller blade in m
+u=%pi*d*N/60;
+beta1=atand(cx/u);
+disp("degree",beta1,"(b)the impeller blade angle at the entry beta1=")
+// part(c)
+cy2=u-(cx/tand(beta2));
+H=n_h*u*cy2/g;
+disp("m",H,"(c)the head developed is")
+//part(d)Power required
+P=(rho*Q*g*H)/(n_o);
+disp("kW",P*1e-3,"(d)Power required to drive the pump is")
+// part(e)
+omega=%pi*2*N/60;
+NS=(H^(-3/4))*0.1804*(omega)*sqrt(Q);
+disp(NS,"(e)the specific speed is")
diff --git a/2223/CH18/EX18.52/Ex18_52.sav b/2223/CH18/EX18.52/Ex18_52.sav
new file mode 100755
index 000000000..d305112ae
--- /dev/null
+++ b/2223/CH18/EX18.52/Ex18_52.sav
diff --git a/2223/CH18/EX18.52/Ex18_52.sce b/2223/CH18/EX18.52/Ex18_52.sce
new file mode 100755
index 000000000..576f2ebb7
--- /dev/null
+++ b/2223/CH18/EX18.52/Ex18_52.sce
@@ -0,0 +1,38 @@
+// scilab Code Exa 18.52 NPSH for Centrifugal pump
+
+H=30; // head developed in m
+ds=0.15; // suction pipe diameter in m
+f=0.005; //Coefficient of friction for the suction pipe
+pa=1.013; // atmospheric pressure in bar
+As=%pi/4*(ds^2); // Cross-sectional Area of the suction pipe in m2
+rho=1e3; // density of water in kg/m3
+g=9.81; // Gravitational acceleration in m/s^2
+t=30; // temperature of water in degree C
+pv=0.0424; // vapour pressure of water at t value
+Hv=pv*1e5/(rho*g);
+Z(1)=0; // altitude in m
+Z(2)=2500;
+p(1)=pa; // at altitude Z=0
+p(2)=0.747; // at Z=2500m
+Q(1)=0.065; // discharge in m3/s of water
+Q(2)=0.1;
+Q(3)=0.15;
+Hs(1)=3; // vertical length of the suction pipe in m
+Hs(2)=5;
+for i=1:3
+    disp("m3/s",Q(i),"when Q=")
+    cs=Q(i)/As;
+    for k=1:2
+        disp("m",Hs(k),"and Hs=")
+        delHf=4*f*(Hs(k)/ds)*(cs^2/(2*g));
+        for j=1:2
+        disp("m",Z(j),"and Z=")
+        Ha=p(j)*1e5/(rho*g);
+    H1=Ha-(Hs(k)+(cs^2/(2*g))+delHf);
+    NPSH=H1-Hv;
+disp(NPSH,"NPSH=")
+sigma=NPSH/H;
+disp(sigma,"Cavitation Coefficient sigma=")
+end
+end
+end
diff --git a/2223/CH18/EX18.53/Ex18_53.sav b/2223/CH18/EX18.53/Ex18_53.sav
new file mode 100755
index 000000000..9b204149b
--- /dev/null
+++ b/2223/CH18/EX18.53/Ex18_53.sav
diff --git a/2223/CH18/EX18.53/Ex18_53.sce b/2223/CH18/EX18.53/Ex18_53.sce
new file mode 100755
index 000000000..f41f1b55d
--- /dev/null
+++ b/2223/CH18/EX18.53/Ex18_53.sce
@@ -0,0 +1,28 @@
+// scilab Code Exa 18.53 NPSH and Thoma Cavitation Coefficient
+
+H=60; // head developed in m
+c1=8; // exit velocity in m/s
+pa=1.0133; // ambient pressure in bar
+rho=1e3;
+n_d=0.8; // Efficiency of the Draft Tube
+g=9.81; // Gravitational acceleration in m/s^2
+ta=30; // ambient temperature of water in degree C
+pv=0.0424; // vapour pressure of water at t value
+Hv=pv*1e5/(rho*g);
+//Q=c1*A1=c2*A2
+Ar(1)=1.2; // draft tube area ratio(A2/A1=c1/c2)
+Ar(2)=1.4;
+Ar(3)=1.6;
+Hs=2.5; // vertical length of the draft tube between the turbine exit and the tail race in m
+Ha=pa*1e5/(rho*g);
+for i=1:3
+    Hsd=(c1^2)*(1-(1/(Ar(i)^2)))/(2*g); // ideal head gained by the draft tube
+    Hd=n_d*Hsd; //Actual head gained by the draft tube
+    disp(Ar(i),"for Area Ratio Ar=")
+    disp("m",Hd,"(a)Actual head gained by the draft tube is")
+    H1=Ha-(Hs+Hd);
+    NPSH=H1-Hv;
+disp(NPSH,"(b)NPSH=")
+sigma=NPSH/H;
+disp(sigma,"and Cavitation parameter(Thoma Number) sigma=")
+end
diff --git a/2223/CH18/EX18.54/Ex18_54.sav b/2223/CH18/EX18.54/Ex18_54.sav
new file mode 100755
index 000000000..59398915d
--- /dev/null
+++ b/2223/CH18/EX18.54/Ex18_54.sav
diff --git a/2223/CH18/EX18.54/Ex18_54.sce b/2223/CH18/EX18.54/Ex18_54.sce
new file mode 100755
index 000000000..b1b8fe578
--- /dev/null
+++ b/2223/CH18/EX18.54/Ex18_54.sce
@@ -0,0 +1,34 @@
+// scilab Code Exa 18.54 Maximum Height of Hydro Turbines
+
+H=52; // head developed in m
+c1=6.5; // exit velocity in m/s
+pa=1.0133; // ambient pressure in bar
+rho=1e3;
+n_d=0.75; // Efficiency of the Draft Tube
+g=9.81; // Gravitational acceleration in m/s^2
+ta=20; // ambient temperature of water in degree C
+sigma_cr=0.1;
+pv=0.023; // vapour pressure of water at t value(from tables)
+Hv=pv*1e5/(rho*g);
+//Q=c1*A1=c2*A2
+Ar=1.5; // draft tube area ratio(A2/A1=c1/c2)
+Z(1)=0; // altitude in m
+Z(2)=2500;
+Z(3)=3000;
+Z(4)=4000;
+p(1)=pa; // at altitude Z=0
+p(2)=0.747; // at Z=2500m
+p(3)=0.701; // at altitude Z=3000m
+p(4)=0.657; // at Z=4000m
+ Hsd=(c1^2)*(1-(1/(Ar^2)))/(2*g); // ideal head gained by the draft tube
+    Hd=n_d*Hsd; //Actual head gained by the draft tube
+Ha=pa*1e5/(rho*g);
+for i=1:4
+        disp("m",Z(i),"For Z=")
+        Ha=p(i)*1e5/(rho*g);
+    H1=Ha-(Hsd+Hd);
+    Hs=Ha-((sigma_cr*H)+Hd+Hv); // vertical length of the draft tube between the turbine exit and the tail race in m
+    disp("m",Hs,"the maximum height of the turbine exit above the tail race is")
+    NPSH=sigma_cr*H;
+disp(NPSH,"NPSH=")
+end
diff --git a/2223/CH18/EX18.55/Ex18_55.sav b/2223/CH18/EX18.55/Ex18_55.sav
new file mode 100755
index 000000000..19412836e
--- /dev/null
+++ b/2223/CH18/EX18.55/Ex18_55.sav
diff --git a/2223/CH18/EX18.55/Ex18_55.sce b/2223/CH18/EX18.55/Ex18_55.sce
new file mode 100755
index 000000000..37d57d471
--- /dev/null
+++ b/2223/CH18/EX18.55/Ex18_55.sce
@@ -0,0 +1,23 @@
+// scilab Code Exa 18.55 Propeller Thrust and Power
+
+c_u=5; // upstream velocity in m/s
+c_s=10; // downstream velocity in m/s
+rho=1e3; // density of water in kg/m3
+c=0.5*(c_u+c_s); // velocity of water through the propeller in m/s
+d(1)=0.5; // propeller diameter in m
+d(2)=1;
+d(3)=1.5;
+delh_0=0.5*((c_s^2)-(c_u^2));
+delp_0=rho*delh_0;
+disp("bar",delp_0*1e-5,"(b)stagnation pressure rise across the propeller is")
+for i=1:3
+    disp("cm",d(i)*1e2,"for propeller diameter=")
+A=%pi*(d(i)^2)/4;
+Q=c*A;
+m=rho*Q;
+disp("m3/s",Q,"(a) flow rate through the propeller is")
+Fx=A*delp_0;
+disp("kN",Fx*1e-3,"(c) thrust exerted by the propeller on the boat is")
+P=m*delh_0;
+disp("kW",P/1000,"(d)the ideal Power required to drive the propeller is")
+end
diff --git a/2223/CH18/EX18.6/Ex18_6.sav b/2223/CH18/EX18.6/Ex18_6.sav
new file mode 100755
index 000000000..14b55d840
--- /dev/null
+++ b/2223/CH18/EX18.6/Ex18_6.sav
diff --git a/2223/CH18/EX18.6/Ex18_6.sce b/2223/CH18/EX18.6/Ex18_6.sce
new file mode 100755
index 000000000..fae4d033b
--- /dev/null
+++ b/2223/CH18/EX18.6/Ex18_6.sce
@@ -0,0 +1,30 @@
+// scilab Code Exa 18.6 Calculations on a Gas Turbine 
+
+m=472; // flow rate of hot gases in kg/s
+T01=1335;  // Turbine inlet temp in Kelvin
+p01=10; // Turbine Inlet Pressure in bar
+c2=150; // exit velocity in m/s
+pr0=10; // Turbine pressure ratio
+gamma_g=1.67;
+T2=560;  // Temperature of gases at exit in Kelvin
+cp_g=1.157; // Specific Heat of gas at Constant Pressure in kJ/(kgK)
+
+// part(a) Determining total to total efficiency
+T02=T2+(0.5*(c2^2)/(cp_g*1e3));
+T02s=T01/(pr0^((gamma_g-1)/gamma_g));
+n_tt=(T01-T02)/(T01-T02s);
+disp("%",n_tt*100,"(a)total to total efficiency is")
+
+
+// part(b) Determining total to static efficiency
+T2s=T02s-(0.5*(c2^2)/(cp_g*1e3));
+n_ts=(T01-T02)/(T01-T2s);
+disp("%",n_ts*100,"(b)total to static efficiency is")
+
+// part(c) Determining the polytropic efficiency
+n_p=((gamma_g)/(gamma_g-1))*((log(T01/T02))/(log(pr0)));
+disp("%",n_p*100,"(c)polytropic efficiency is")
+
+// part(d) Determining power developed by the turbine
+P=m*cp_g*(T01-T02);
+disp("MW",P/1e3,"(d)Power developed by the turbine is")
diff --git a/2223/CH18/EX18.7/Ex18_7.sav b/2223/CH18/EX18.7/Ex18_7.sav
new file mode 100755
index 000000000..7e0a15356
--- /dev/null
+++ b/2223/CH18/EX18.7/Ex18_7.sav
diff --git a/2223/CH18/EX18.7/Ex18_7.sce b/2223/CH18/EX18.7/Ex18_7.sce
new file mode 100755
index 000000000..cbf36c7ff
--- /dev/null
+++ b/2223/CH18/EX18.7/Ex18_7.sce
@@ -0,0 +1,25 @@
+// scilab Code Exa 18.7 RHF of a three stage turbine
+
+p1=1.0; // Initial Pressure in bar
+gamma=1.4;
+T1=1500;  // Initial Temperature in K
+s=3; // number of stages
+opr=11; // Overall Pressure Ratio
+pr=opr^(1/s); // equal Pressure Ratio in each stage
+n_T=0.88; // Overall Efficiency 
+delTa=T1*(1-opr^(-((gamma-1)/gamma)))*n_T;
+T2=T1-delTa;
+n_p=(log(T1/T2))/(((gamma-1)/gamma)*(log(opr))); // polytropic or small stage efficiency
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+n_st=(1-pr^(n_p*(-((gamma-1)/gamma))))/(1-pr^(-((gamma-1)/gamma))); // stage efficiency
+T(1)=T1;
+for i=1:3
+    delT(i)=T(i)*(1-pr^(n_p*(-((gamma-1)/gamma))));
+    delw_s(i)=delT(i)*cp/n_st;
+    T(i+1)=T(i)-delT(i);
+end
+w_a=cp*delTa;
+w_s=w_a/n_T;
+RHF=(delw_s(1)+delw_s(2)+delw_s(3))/w_s;
+disp(RHF,"the reheat factor is")
+
diff --git a/2223/CH18/EX18.8/Ex18_8.sav b/2223/CH18/EX18.8/Ex18_8.sav
new file mode 100755
index 000000000..0fa3ca754
--- /dev/null
+++ b/2223/CH18/EX18.8/Ex18_8.sav
diff --git a/2223/CH18/EX18.8/Ex18_8.sce b/2223/CH18/EX18.8/Ex18_8.sce
new file mode 100755
index 000000000..b39ea15f3
--- /dev/null
+++ b/2223/CH18/EX18.8/Ex18_8.sce
@@ -0,0 +1,35 @@
+// scilab Code Exa 18.8 Calculation on an air compressor
+
+funcprot(0)
+p1=1.0; // Initial Pressure in bar
+T1=305;  // Initial Temperature in degree K
+k=16; // number of stages
+m=400; // mass flow rate through the compressor in kg/s
+p_rc=10; // overall Pressure Ratio
+gamma=1.4; // Specific Heat Ratio
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+n_p=0.88; // polytropic efficiency
+
+// part(a) Determining stage Pressure Ratio
+pr=p_rc^(1/k);
+disp(pr,"(a)stage Pressure Ratio is")
+
+// part(b) Determining the stage efficiency
+T2s=T1*(pr^((gamma-1)/gamma));
+T2=T1*(pr^((gamma-1)/(gamma*n_p)));
+n_st=(T2s-T1)/(T2-T1);
+disp("%",n_st*100,"(b)stage Efficiency of the compressor is")
+
+// part(c) Determining power required for the first stage
+P1=m*cp*(T2-T1);
+disp ("MW",P1/1e3,"(c)Power required for the first stage is")
+
+// part(d)Overall Compressor Efficiency
+T17=T1*exp(((gamma-1)/(gamma*n_p))*(log(p_rc))); // k+1=17;
+T17s=T1*(p_rc^((gamma-1)/gamma));
+n_C=(T17s-T1)/(T17-T1);
+disp ("%",n_C*100,"(d)Overall Compressor Efficiency is")
+
+// part(e) Determining power required to drive the compressor
+P=m*cp*(T17-T1);
+disp ("MW",P/1e3,"(e)Power required to drive the compressor is")
diff --git a/2223/CH18/EX18.9/Ex18_9.sav b/2223/CH18/EX18.9/Ex18_9.sav
new file mode 100755
index 000000000..ed8a93741
--- /dev/null
+++ b/2223/CH18/EX18.9/Ex18_9.sav
diff --git a/2223/CH18/EX18.9/Ex18_9.sce b/2223/CH18/EX18.9/Ex18_9.sce
new file mode 100755
index 000000000..4e07f3e37
--- /dev/null
+++ b/2223/CH18/EX18.9/Ex18_9.sce
@@ -0,0 +1,50 @@
+// scilab Code Exa 18.9 Constant Pressure Gas Turbine Plant
+
+T1=298; // Minimum Temperature in Kelvin
+beeta=4.5; // Maximum to Minimum Temperature ratio(T_max/T_min)
+m=115; // mass flow rate through the turbine and compressor in kg/s
+n_C=0.79; // Compressor Efficiency
+n_T=0.83; // Turbine Efficiency
+gamma_g=1.33;
+R=0.287;
+cp=(gamma_g/(gamma_g-1))*R; // Specific Heat at Constant Pressure in kJ/(kgK)
+alpha=beeta*n_C*n_T;
+t_opt=sqrt(alpha); // For maximum power output, the temperature ratios in the turbine and compressor
+
+// part(a) Determining optimum pressure ratio of the plant
+r=t_opt^(gamma_g/(gamma_g-1));
+disp(r,"(a)optimum pressure ratio of the plant is")
+
+// part(b)Carnot's efficiency
+n_Carnot=1-(1/beeta);
+disp("%",n_Carnot*100,"(b)Carnot efficiency of the plant is")
+
+// part(c) Determining Joule's cycle efficiency
+n_Joule=1-(1/t_opt);
+disp("%",n_Joule*100,"(c)efficiency of the Joule cycle is")
+
+// part(d) Determining thermal efficiency of the plant for maximum power output
+n_th=(t_opt-1)^2/((beeta-1)*n_C-(t_opt-1));
+disp("%",n_th*100,"(d)thermal efficiency of the plant for maximum power output is")
+
+// part(e) Determining power output
+wp_max=cp*T1*((t_opt-1)^2)/n_C; // maximum work output
+P_max=m*wp_max;
+disp ("MW",P_max/1e3,"(e)Power output is")
+
+// part(f) Determining power generated by the turbine required to drive the compressor
+T3=beeta*T1;  // Maximum Temperature in degree K
+T4s=T3*(r^(-((gamma_g-1)/gamma_g)));
+T4=T3-((T3-T4s)*n_T);
+P_T=m*cp*(T3-T4);
+disp ("MW",P_T/1e3,"(f)Power generated by the turbine is")
+
+// part(g) Determining power absorbed by the compressor
+T2s=T1*(r^((gamma_g-1)/gamma_g));
+T2=T1+((T2s-T1)/n_C);
+P_C=m*cp*(T2-T1);
+disp ("MW",P_C/1e3,"(g)Power absorbed by the compressor is")
+
+//part(h)heat supplied in the combustion chamber
+Qs=m*cp*(T3-T2);
+disp("MW",Qs/1e3,"(h)heat supplied in the combustion chamber is")
diff --git a/2223/CH2/EX2.1/Ex2_1.sav b/2223/CH2/EX2.1/Ex2_1.sav
new file mode 100755
index 000000000..9152585ab
--- /dev/null
+++ b/2223/CH2/EX2.1/Ex2_1.sav
diff --git a/2223/CH2/EX2.1/Ex2_1.sce b/2223/CH2/EX2.1/Ex2_1.sce
new file mode 100755
index 000000000..0528ccd2c
--- /dev/null
+++ b/2223/CH2/EX2.1/Ex2_1.sce
@@ -0,0 +1,26 @@
+// scilab Code Exa 2.1 Calculation on a Diffuser 
+
+p1=800; // Initial Pressure in kPa
+T1=540;  // Initial Temperature in K
+p2=580;  // Final Pressure in kPa
+gamma=1.4; // Specific Heat Ratio
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=0.287; // Universal Gas Constant in kJ/kgK
+g=9.81; // Gravitational acceleration in m/s^2
+sg=13.6; // Specific Gravity of mercury
+n=0.95; // Efficiency in %
+AR=4; // Area Ratio of Diffuser
+delp=(367)*(1e-3)*(g)*(sg); // Total Pressure Loss Across the Diffuser in kPa
+pr=p1/p2; // Pressure Ratio
+T2s=T1/(pr^((gamma-1)/gamma));
+T2=T1-(n*(T1-T2s));
+c2=sqrt(2*cp*(T1-T2));
+ro2=p2/(R*T2);
+c3=c2/AR;
+m=0.5*1e-3*ro2*((c2^2)-(c3^2));
+n_D=1-(delp/m);
+disp ("%",n_D*1e2," Efficiency of the diffuser is")
+p3=(p2+n_D*m)*1e-2;
+disp("m/s",c2,"the velocity of air at diffuser entry is")
+disp("m/s",c3,"the velocity of air at diffuser exit is")
+disp("bar",p3,"static pressure at the diffuser exit is")
diff --git a/2223/CH2/EX2.2/Ex2_2.sav b/2223/CH2/EX2.2/Ex2_2.sav
new file mode 100755
index 000000000..7fd7bfb1e
--- /dev/null
+++ b/2223/CH2/EX2.2/Ex2_2.sav
diff --git a/2223/CH2/EX2.2/Ex2_2.sce b/2223/CH2/EX2.2/Ex2_2.sce
new file mode 100755
index 000000000..fdebe6df4
--- /dev/null
+++ b/2223/CH2/EX2.2/Ex2_2.sce
@@ -0,0 +1,27 @@
+// Exa 2.2 Determining the infinitesimal stage efficiencies
+p1=1.02; // Initial Pressure in bar
+T1=300;  // Initial Temperature in K
+
+// part(a)
+T2=315;  // Final Temperature in K
+gamma=1.4; // Specific Heat Ratio
+g=9.81; // Gravitational acceleration in m/s^2
+sg=1; // Specific Gravity of air
+delp=(1500)*(0.001)*(g)*(sg); // Total Pressure Loss Across the Diffuser in kPa
+p2=p1+(0.01*delp);
+pr=p2/p1; // Pressure Ratio
+T2s=T1*(pr^((gamma-1)/gamma));
+n_c=(T2s-T1)/(T2-T1); // Efficiency in %
+n_p=((gamma-1)/gamma)*((log(p2/p1))/(log(T2/T1)));
+disp ("%",n_c*100,"(a)Efficiency of the compressor is")
+disp ("%",n_p*100,"and infinitesimal stage Efficiency or polytropic efficiency of the compressor is")
+
+// part(b) Determining the infinitesimal stage efficiency
+
+p2_b=2.5;  // Final pressure in bar
+n_b=0.75; // Efficiency
+pr_b=p2_b/p1; // Pressure Ratio
+T2s_b=T1*(pr_b^((gamma-1)/gamma));
+T2_b=T1+((T2s_b-T1)/n_b);
+n_p_b=((gamma-1)/gamma)*((log(p2_b/p1))/(log(T2_b/T1)));
+disp ("%" ,n_p_b*100,"(b)infinitesimal stage Efficiency or polytropic efficiency of the compressor is")
diff --git a/2223/CH2/EX2.3/Ex2_3.sav b/2223/CH2/EX2.3/Ex2_3.sav
new file mode 100755
index 000000000..d2db3d784
--- /dev/null
+++ b/2223/CH2/EX2.3/Ex2_3.sav
diff --git a/2223/CH2/EX2.3/Ex2_3.sce b/2223/CH2/EX2.3/Ex2_3.sce
new file mode 100755
index 000000000..7e2bfda9e
--- /dev/null
+++ b/2223/CH2/EX2.3/Ex2_3.sce
@@ -0,0 +1,31 @@
+// scilab Code Exa 2.3 Calculation on a compressor
+p1=1.0; // Initial Pressure in bar
+t1=40;  // Initial Temperature in degree C
+T1=t1+273; // in Kelvin
+s=8; // number of stages
+m=50; // mass flow rate through the compressor in kg/s
+pr=1.35; // equal Pressure Ratio in each stage
+opr=pr^s; // Overall Pressure Ratio
+gamma=1.4; // Specific Heat Ratio
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+n=0.82; // Overall Efficiency
+
+// part(a) Determining state of air at the compressor exit
+p9=opr*p1;
+delTc=T1*(opr^((gamma-1)/gamma)-1)/n;
+T9=T1+delTc;
+disp("bar",p9,"(a)Exit Pressure is")
+disp("K",T9,"and Exit Temperature is")
+
+// part(b) Determining the polytropic or small stage efficiency
+n_p=((gamma-1)/gamma)*((log(p9/p1))/(log(T9/T1)));
+disp("%",n_p*100,"(b)small stage Efficiency or polytropic efficiency of the compressor is")
+
+// part(c) Determining efficiency of each stage
+n_st=(pr^((gamma-1)/gamma)-1)/(pr^(((gamma-1)/gamma)/n_p)-1);
+disp ("%",n_st*100,"(c)Efficiency of each stage is")
+
+// part(d) Determining power required to drive the compressor
+n_d=0.9; // Overall efficiency of the drive
+P=m*cp*delTc/n_d;
+disp ("MW" ,P/1e3,"(d)Power required to drive the compressor is")
diff --git a/2223/CH2/EX2.4/Ex2_4.sav b/2223/CH2/EX2.4/Ex2_4.sav
new file mode 100755
index 000000000..4ce0c9a9a
--- /dev/null
+++ b/2223/CH2/EX2.4/Ex2_4.sav
diff --git a/2223/CH2/EX2.4/Ex2_4.sce b/2223/CH2/EX2.4/Ex2_4.sce
new file mode 100755
index 000000000..4d96299da
--- /dev/null
+++ b/2223/CH2/EX2.4/Ex2_4.sce
@@ -0,0 +1,25 @@
+// Exa 2.4 compressor with same temperature rise
+
+p1=1.0; // Initial Pressure in bar
+t1=40;  // Initial Temperature in degree C
+T1=t1+273; // in Kelvin
+s=8; // number of stages
+pr=1.35;
+opr=pr^s; // Overall Pressure Ratio
+n=0.82; // Overall Efficiency 
+p9=opr*p1;
+gamma=1.4;
+delTc=(T1*(opr^((gamma-1)/gamma)-1)/n);
+delTi=delTc/s;
+T9=T1+delTc;
+n_p=((gamma-1)/gamma)*((log(p9/p1))/(log(T9/T1))); // small stage Efficiency or polytropic efficiency
+m=8;
+T(1)=T1;
+for i=1:m
+    T(i+1)=T(i)+delTi;
+    pr(i)=(1+(delTi/T(i)))^(n_p/((gamma-1)/gamma));
+    n_st(i)=(pr(i)^((gamma-1)/gamma)-1)/(pr(i)^(((gamma-1)/gamma)/n_p)-1);
+disp(T(i),"T is");
+disp(pr(i),"pressure ratio is")
+disp(n_st(i),"efficiency is" )
+end
diff --git a/2223/CH2/EX2.5/Ex2_5.sav b/2223/CH2/EX2.5/Ex2_5.sav
new file mode 100755
index 000000000..b219f9f80
--- /dev/null
+++ b/2223/CH2/EX2.5/Ex2_5.sav
diff --git a/2223/CH2/EX2.5/Ex2_5.sce b/2223/CH2/EX2.5/Ex2_5.sce
new file mode 100755
index 000000000..ad8c3fb99
--- /dev/null
+++ b/2223/CH2/EX2.5/Ex2_5.sce
@@ -0,0 +1,37 @@
+// scilab Code Exa 2.5 Calculation on three stage gas turbine
+
+p1=1.0; // Initial Pressure in bar
+gamma=1.4;
+T1=1500;  // Initial Temperature in K
+s=3; // number of stages
+opr=11; // Overall Pressure Ratio
+
+// part(a)Determining pressure ratio of each stage
+pr=opr^(1/s); // equal Pressure Ratio in each stage
+disp (pr,"(a)Pressure ratio of each stage is")
+
+// part(b)Determining the polytropic or small stage efficiency
+n_o=0.88; // Overall Efficiency 
+delT=T1*(1-opr^(-((gamma-1)/gamma)))*n_o;
+T2=T1-delT;
+n_p=(log(T1/T2))/(((gamma-1)/gamma)*(log(opr)));
+disp ("%",n_p*100,"(b)small stage Efficiency or polytropic efficiency of the turbine is")
+
+// part(c) Determining mass flow rate
+P=30000; // Power output of the Turbine in kW
+n_d=0.91; // Overall efficiency of the drive
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+m=P/(cp*delT*n_d);
+disp ("kg/s",m,"(c)mass flow rate is")
+
+// part(d) Determining efficiency of each stage
+n_st=(1-pr^(n_p*(-((gamma-1)/gamma))))/(1-pr^(-((gamma-1)/gamma)));
+disp ("%",n_st*100,"(d)Efficiency of each stage is")
+d=3;
+T(1)=T1;
+for i=1:d
+    delT(i)=T(i)*(1-pr^(n_p*(-((gamma-1)/gamma))));
+    T(i+1)=T(i)-delT(i);
+    P(i)=m*cp*delT(i);
+printf("\n P(%d)=%f MW",i,P(i)*1e-3)
+end
diff --git a/2223/CH2/EX2.6/Ex2_6.sav b/2223/CH2/EX2.6/Ex2_6.sav
new file mode 100755
index 000000000..6afab9df9
--- /dev/null
+++ b/2223/CH2/EX2.6/Ex2_6.sav
diff --git a/2223/CH2/EX2.6/Ex2_6.sce b/2223/CH2/EX2.6/Ex2_6.sce
new file mode 100755
index 000000000..416fc5bd7
--- /dev/null
+++ b/2223/CH2/EX2.6/Ex2_6.sce
@@ -0,0 +1,37 @@
+// scilab Code Exa 2.6 calculation on a gas turbine
+
+funcprot(0);
+p1=5; // Inlet Pressure in bar
+p2=1.2; // Exit Pressure in bar
+T1=500;  // Initial Temperature in K
+gamma=1.4;
+m=20; // mass flow rate of the gas in kg/s
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+n_T=0.9; // Overall Efficiency 
+pr=p1/p2; // Pressure Ratio
+// part(a)
+T2s=T1/(pr^((gamma-1)/gamma));
+T2=T1-(n_T*(T1-T2s));
+n_p=(log(T1/T2))/(log(T1/T2s));
+disp("%",n_p*100,"(a)small stage Efficiency or polytropic efficiency of the expansion is")
+P=m*cp*(T1-T2);
+disp("kW",P,"and Power developed is")
+
+// part(b)
+AR=2.5; // Area Ratio of Diffuser
+R=0.287; // Universal Gas Constant in kJ/kgK
+p3=1.2; // Exit Pressure for diffuser in bar
+c2=75; // Velocity of gas at turbine exit in m/s
+c3=c2/AR;
+n_d=0.7; // Efficiency of the diffuser
+ro2=p2/(R*T2);
+delp=n_d*(0.5*0.001*ro2*((c2^2)-(c3^2))); // delp=p3-p2d
+disp("mm W.G.",delp*100000/9.81,"(b)static pressure across the diffuser is")
+p2d=p3-delp;
+prd=p1/p2d;
+T2sd=T1/(prd^((gamma-1)/gamma));
+T2d=T1-(n_T*(T1-T2sd));
+Pd=m*cp*(T1-T2d);
+disp("kW",Pd-P,"and Increase in the power output of the turbine is")
+
+disp("Comment: Error in Textbook, Answers vary due to Round-off Errors")
diff --git a/2223/CH3/EX3.1/Ex3_1.sav b/2223/CH3/EX3.1/Ex3_1.sav
new file mode 100755
index 000000000..792c1b874
--- /dev/null
+++ b/2223/CH3/EX3.1/Ex3_1.sav
diff --git a/2223/CH3/EX3.1/Ex3_1.sce b/2223/CH3/EX3.1/Ex3_1.sce
new file mode 100755
index 000000000..adcbf9c38
--- /dev/null
+++ b/2223/CH3/EX3.1/Ex3_1.sce
@@ -0,0 +1,25 @@
+// scilab Code Exa 3.1 Constant Pressure Gas Turbine Plant
+
+t1=50;  // Minimum Temperature in degree C
+T1=t1+273; // in Kelvin
+t3=950;  // Maximum Temperature in degree C
+T3=t3+273; // in Kelvin
+n_c=0.82; // Compressor Efficiency
+n_t=0.87; // Turbine Efficiency
+gamma=1.4; // Specific Heat Ratio
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+beeta=T3/T1;
+alpha=beeta*n_c*n_t;
+T_opt=sqrt(alpha); // For maximum power output, the temperature ratios in the turbine and compressor
+
+// part(a) Determining pressure ratio of the turbine and compressor
+pr=T_opt^(gamma/(gamma-1));
+disp(pr,"(a)Pressure Ratio is")
+
+// part(b) Determining maximum power output per unit flow rate
+wp_max=cp*T1*((T_opt-1)^2)/n_c;
+disp("kW/(kg/s)",wp_max,"(b)maximum power output per unit flow rate is")
+
+// part(c) Determining thermal efficiency of the plant for maximum power output
+n_th=(T_opt-1)^2/((beeta-1)*n_c-(T_opt-1));
+disp("%",n_th*100,"(c)thermal efficiency of the plant for maximum power output is")
diff --git a/2223/CH3/EX3.2/Ex3_2.sav b/2223/CH3/EX3.2/Ex3_2.sav
new file mode 100755
index 000000000..4dfccdf81
--- /dev/null
+++ b/2223/CH3/EX3.2/Ex3_2.sav
diff --git a/2223/CH3/EX3.2/Ex3_2.sce b/2223/CH3/EX3.2/Ex3_2.sce
new file mode 100755
index 000000000..d76388239
--- /dev/null
+++ b/2223/CH3/EX3.2/Ex3_2.sce
@@ -0,0 +1,38 @@
+// scilab Code Exa 3.2 Gas Turbine Plant with an exhaust HE
+T1=300;  // Minimum  cycle Temperature in Kelvin
+funcprot(0);
+pr=10; // pressure ratio of the turbine and compressor
+T3=1500;  // Maximum cycle Temperature in Kelvin
+m=10; // mass flow rate through the turbine and compressor in kg/s
+e(1)=0.8; // thermal ratio of the heat exchanger
+e(2)=1;
+n_c=0.82; // Compressor Efficiency
+n_t=0.85; // Turbine Efficiency
+gamma=1.4; // Specific Heat Ratio
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+beeta=T3/T1;
+T2s=T1*(pr^((gamma-1)/gamma));
+T2=T1+((T2s-T1)/n_c);
+T4s=T3*(pr^(-((gamma-1)/gamma)));
+T4=T3-((T3-T4s)*n_t);
+
+for i=1:2
+T5=T2+e(i)*(T4-T2);
+T6=T4-(T5-T2);
+Q_s=cp*(T3-T5);
+Q_r=cp*(T6-T1);
+// part(a) Determining power developed
+w_p=Q_s-Q_r;
+P=m*w_p;
+printf("for effectiveness=%f, \n (a)the power developed is %f kW",e(i),P)
+
+// part(b) Determining thermal efficiency of the plant
+n_th=1-(Q_r/Q_s);
+disp ("%",n_th*100,"(b)thermal efficiency of the plant is")    
+end
+
+// part(c) Determining efficiencies of the ideal Joules cycle
+n_Joule=1-(pr^((gamma-1)/gamma)/beeta);
+disp("%",n_Joule*100,"(c)efficiency of the ideal Joules cycle with perfect heat exchange is")
+n_Carnot=1-(T1/T3);
+disp("%",n_Carnot*100,"and the Carnot cycle efficiency is")
diff --git a/2223/CH3/EX3.3/Ex3_3.sav b/2223/CH3/EX3.3/Ex3_3.sav
new file mode 100755
index 000000000..bb26e4468
--- /dev/null
+++ b/2223/CH3/EX3.3/Ex3_3.sav
diff --git a/2223/CH3/EX3.3/Ex3_3.sce b/2223/CH3/EX3.3/Ex3_3.sce
new file mode 100755
index 000000000..56681d5dc
--- /dev/null
+++ b/2223/CH3/EX3.3/Ex3_3.sce
@@ -0,0 +1,19 @@
+// scilab Code Exa 3.3 ideal reheat cycle gas turbine
+T1=300;  // Minimum  cycle Temperature in Kelvin
+r=25; // pressure ratio of the turbine and compressor
+gamma=1.4;
+T3=1500;  // Maximum cycle Temperature in Kelvin
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+beeta=T3/T1;
+n=(gamma-1)/gamma;
+t=(r^n);
+d=1/sqrt(t);
+// part(a) Determining mass flow rate through the turbine and compressor
+c=2*beeta*[1-d];
+wp_max=cp*T1*(c+1-t);
+m=1000/wp_max;
+disp ("kg/s",m,"(a)mass flow rate through the turbine and compressor is")
+
+// part(b) Determining thermal efficiency of the plant
+n_th=(c+1-t)/(2*beeta-t-(beeta/sqrt(t)));
+disp ("%",n_th*100,"(b)thermal efficiency of the plant is")    
diff --git a/2223/CH3/EX3.4/Ex3_4.sav b/2223/CH3/EX3.4/Ex3_4.sav
new file mode 100755
index 000000000..6768f704e
--- /dev/null
+++ b/2223/CH3/EX3.4/Ex3_4.sav
diff --git a/2223/CH3/EX3.4/Ex3_4.sce b/2223/CH3/EX3.4/Ex3_4.sce
new file mode 100755
index 000000000..aa3a340fe
--- /dev/null
+++ b/2223/CH3/EX3.4/Ex3_4.sce
@@ -0,0 +1,21 @@
+// scilab Code Exa 3.4 Calculations on Gas Turbine Plant for an ideal reheat cycle with optimum reheat pressure and perfect exhaust heat exchange
+T1=300;  // Minimum  cycle Temperature in Kelvin
+r=25; // pressure ratio of the turbine and compressor
+T3=1500;  // Maximum cycle Temperature in Kelvin
+gamma=1.4; // Specific Heat Ratio
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+beeta=T3/T1;
+n=(gamma-1)/gamma;
+t=(r^n);
+d=1/sqrt(t);
+// part(a) Determining mass flow rate through the turbine and compressor
+c=2*beeta*[1-d];
+wp_max=cp*T1*(c+1-t);
+m=1000/wp_max;
+disp ("kg/s" ,m," mass flow rate through the turbine and compressor is")
+
+
+// part(b) Determining thermal efficiency of the plant
+c=sqrt(t)*(sqrt(t)+1)/(2*beeta);
+n_th=1-c;
+disp ("%",n_th*100," thermal efficiency of the plant is")    
diff --git a/2223/CH3/EX3.5/Ex3_5.sav b/2223/CH3/EX3.5/Ex3_5.sav
new file mode 100755
index 000000000..c8cc278da
--- /dev/null
+++ b/2223/CH3/EX3.5/Ex3_5.sav
diff --git a/2223/CH3/EX3.5/Ex3_5.sce b/2223/CH3/EX3.5/Ex3_5.sce
new file mode 100755
index 000000000..f2c6cb2b6
--- /dev/null
+++ b/2223/CH3/EX3.5/Ex3_5.sce
@@ -0,0 +1,61 @@
+// scilab Code Exa 3.5 Calculations on Gas Turbine Plant 
+
+P=10e4; // Power Output in kW
+T1=310;  // Minimum  cycle Temperature in Kelvin
+p1=1.013; // Compressor Inlet Pressure in bar
+pr_c=8; // Compressor pressure ratio
+gamma=1.4;
+gamma_g=1.33;
+R=0.287; 
+p2=pr_c*p1; // Compressor Exit Pressure in bar
+T3=1350;  // Maximum cycle Temperature(Turbine inlet temp) in Kelvin
+n_c=0.85; // Compressor Efficiency
+p3=0.98*p2; // turbine inlet pressure
+p4=1.02; // turbine exit pressure in bar
+CV=40*10e2; // Calorific Value of fuel in kJ/kg;
+n_B=0.98; // Combustion Efficiency
+n_m=0.97; // Mechanical efficiency
+n_t=0.9; // Turbine Efficiency
+n_G=0.98; // Generator Efficiency
+cp_a=1.005; // Specific Heat of air at Constant Pressure in kJ/(kgK)
+
+// Air Compressor
+T2s=T1*(pr_c^((gamma-1)/gamma));
+T2=T1+((T2s-T1)/n_c);
+w_c=cp_a*(T2-T1);
+
+// Gas Turbine
+n_g=(gamma_g-1)/gamma_g;
+cp_g=1.157; // Specific Heat of gas at Constant Pressure in kJ/(kgK)
+pr_t=p3/p4;
+T4s=T3/(pr_t^((gamma_g-1)/gamma_g));
+T4=T3-(n_t*(T3-T4s));
+w_t=cp_g*(T3-T4);
+w_net=w_t-w_c;
+w_g=n_m*n_G*w_net;
+
+// part(a) Determining Gas Flow Rate
+m_g=P/w_g;
+disp ("kg/s",m_g,"(a)Gas flow rate is")
+
+// part(b) Determining Fuel-Air Ratio
+F_A=((cp_g*T3)-(cp_a*T2))/((CV*n_B)-(cp_g*T3));
+disp(F_A,"(b)Fuel-Air Ratio is")
+
+// part(c) Air flow rate
+m_a=m_g/(1+F_A);
+disp("kg/s",m_a,"(c)Air flow rate is")
+
+// part(d) Determining thermal efficiency of the plant
+m_f=m_g-m_a;
+n_th=m_g*w_net/(m_f*CV);
+disp ("%",n_th*100,"(d)thermal efficiency of the plant is")
+
+// part(e) Determining Overall efficiency of the plant
+n_o=n_m*n_G*n_th;
+disp ("%",n_o*100,"(e)overall efficiency of the plant is")
+
+// part(f) Determining ideal Joule cycle efficiency
+n_Joule=1-(1/(pr_c^((gamma-1)/gamma)));
+disp ("%",n_Joule*100,"(f)efficiency of the ideal Joule cycle is")
+
diff --git a/2223/CH4/EX4.1/Ex4_1.sav b/2223/CH4/EX4.1/Ex4_1.sav
new file mode 100755
index 000000000..1a62e541a
--- /dev/null
+++ b/2223/CH4/EX4.1/Ex4_1.sav
diff --git a/2223/CH4/EX4.1/Ex4_1.sce b/2223/CH4/EX4.1/Ex4_1.sce
new file mode 100755
index 000000000..ae20d5012
--- /dev/null
+++ b/2223/CH4/EX4.1/Ex4_1.sce
@@ -0,0 +1,45 @@
+// scilab Code Exa 4.1 Calculations on Steam Turbine Plant 
+
+p1=25; // Turbine Inlet Pressure in bar
+p2=0.065;  // Condenser Pressure in bar
+n_B=0.82; // Boiler efficiency
+delp=p1-p2;
+v_w=0.001; // Specific Volume at condenser Pressure in m3/kg
+
+h1=160.6; // from steam tables at p1=0.065 bar
+h2=h1+(delp*100*v_w);
+
+//part(a) Determining exact and approximate Rankine efficiency of the plant
+h3=2800; // from steam table vapour enthalpy at 25 bar
+h4=1930; // from steam table
+n_rankine_ex=(h3-h4-(h2-h1))/(h3-h1-(h2-h1));
+disp ("%",n_rankine_ex*100,"(a)(i) Exact Rankine efficiency is")
+
+n_rankine_app=(h3-h4)/(h3-h1);
+disp ("%",n_rankine_app*100," (a)(ii)Approximate Rankine efficiency is")
+
+//part(b) Determining thermal and relative efficiencies of the plant
+n_t=0.78; // Turbine Efficiency
+CV=26.3*10e2; // Calorific Value of fuel in kJ/kg;
+n_th=(n_t*(h3-h4))/(h3-h1);
+disp("%",n_th*100,"(b)(i)thermal efficiency of the plant is")
+n_rel=n_th/n_rankine_app;
+disp("%",n_rel*100,"(ii)relative efficiency of the plant is")
+
+//part(c) Determining Overall efficiency of the plant
+n_o=n_th*n_B;
+disp("%",n_o*100,"(c)overall efficiency of the plant is")
+
+//part(d) Turbine and Overall heat rates
+hr_t=3600/n_th; 
+disp("kJ/kWh",hr_t,"(d)(i)Turbine Heat Rate is")
+hr_o=3600/n_o; 
+disp("kJ/kWh",hr_o,"(d)(ii)overall Heat Rate is")
+
+//part(e) Steam Consumption per kWh
+m_s=3600/(n_t*(h3-h4));
+disp("kg/kWh" ,m_s,"(e)Steam Consumption is")
+
+//part(f) Fuel Consumption per kWh
+m_f=3600/(CV*n_o);
+disp("kg/kWh" ,m_f,"(f)Fuel Consumption is")
diff --git a/2223/CH4/EX4.2/Ex4_2.sav b/2223/CH4/EX4.2/Ex4_2.sav
new file mode 100755
index 000000000..bf41820d2
--- /dev/null
+++ b/2223/CH4/EX4.2/Ex4_2.sav
diff --git a/2223/CH4/EX4.2/Ex4_2.sce b/2223/CH4/EX4.2/Ex4_2.sce
new file mode 100755
index 000000000..c68c2c072
--- /dev/null
+++ b/2223/CH4/EX4.2/Ex4_2.sce
@@ -0,0 +1,52 @@
+
+// scilab Code Exa 4.2 Steam Turbine Plant for different reheat cycles
+
+p1=160; // Turbine Inlet Pressure in bar
+T1=500;  // Turbine Entry Temperature in Degree Celsius
+p2=0.06;  // Condenser Pressure in bar
+
+// from steam tables at p1=0.06 bar, 
+h1=147; // Specific Enthalpy of water in kJ/kg
+h2=2567; // Specific Enthalpy of steam in kJ/kg
+
+h3=3295; // from steam table
+h4=1947; // from steam table
+q_n=h3-h1;
+n_N=(h3-h4)/(q_n);
+x=(h4-h1)/(h2-h1);
+disp("%",n_N*100,"for non reheat cycle plant efficiency is")
+disp ("kJ/kWh",3600/n_N,"Turbine Heat Rate is")
+disp(x,"final dryness fraction is")
+// for reheat cycle
+
+p(1)=70;
+h5(1)=3412; // in kJ/kg
+h7(1)=3065; // in kJ/kg
+h6(1)=2094; // in kJ/kg
+p(2)=50;
+h5(2)=3433; // in kJ/kg
+h7(2)=2981; // in kJ/kg
+h6(2)=2144; // in kJ/kg
+p(3)=25;
+h5(3)=3475; // in kJ/kg
+h7(3)=2826; // in kJ/kg
+h6(3)=2249; // in kJ/kg
+for i=1:3
+ q_r(i)=h5(i)-h7(i);
+a(i)=(h6(i)-h4)/(q_r(i));
+n_r(i)=1-a(i); // exact Rankine efficiency
+b(i)=q_r(i)*n_r(i)/n_N;
+n_th(i)=(q_n+b(i))*n_N/(q_n+q_r(i));
+hr_t(i)=3600/n_th(i);
+x(i)=(h6(i)-h1)/(h2-h1);
+disp("bar",p(i),"for reheat pressure" )
+disp("kJ",q_r(i),"q_R=")
+disp("kJ",h6(i)-h4,"H6-H4= ")
+disp("%",n_r(i)*100,"Rankine efficiency of the plant is")
+disp("%",n_th(i)*100,"thermal efficiency of the plant is")
+disp("kJ/kWh",hr_t(i),"Heat Rate is")
+disp(x(i),"final dryness fraction is")
+   
+end
+
+disp("Comment: Error in Textbook, Answers vary due to Round-off Errors")
diff --git a/2223/CH4/EX4.3/Ex4_3.sav b/2223/CH4/EX4.3/Ex4_3.sav
new file mode 100755
index 000000000..a505db570
--- /dev/null
+++ b/2223/CH4/EX4.3/Ex4_3.sav
diff --git a/2223/CH4/EX4.3/Ex4_3.sce b/2223/CH4/EX4.3/Ex4_3.sce
new file mode 100755
index 000000000..97acd7278
--- /dev/null
+++ b/2223/CH4/EX4.3/Ex4_3.sce
@@ -0,0 +1,73 @@
+// scilab Code Exa 4.3 Calculations on Steam Turbine Plant 
+
+p1=82.75; // Turbine Inlet Pressure in bar
+T1=510;  // Turbine Entry Temperature in Degree Celsius
+pc=0.042;  // Condenser Pressure in bar
+H=3420;
+n_e=0.85;
+gamma=1.4;
+n_st1=0.85;
+
+p2=22.75;
+// for regenerative cycle
+hs(1)=121.4; // from steam tables and mollier chart
+p(6)=p2; // pressure at bleed point 1
+Hs(6)=3080; // Enthalpy of steam at bleed point 1
+h1s=931;
+hs(6)=h1s; // Enthalpy of water at bleed point 1
+H_22=H-(n_st1*(H-h1s));
+
+p(5)=10.65; // pressure at bleed point 2
+Hs(5)=2950; // Enthalpy of steam at bleed point 2
+hs(5)=772; // Enthalpy of water at bleed point 2
+
+p(4)=4.35; // pressure at bleed point 3
+Hs(4)=2730; // Enthalpy of steam at bleed point 3
+hs(4)=612; // Enthalpy of water at bleed point 3
+
+p(3)=1.25; // pressure at bleed point 4
+Hs(3)=2590; // Enthalpy of steam at bleed point 4
+hs(3)=444; // Enthalpy of water at bleed point 4
+
+p(2)=0.6; // pressure at bleed point 5
+Hs(2)=2510; // Enthalpy of steam at bleed point 5
+hs(2)=360; // Enthalpy of water at bleed point 5
+
+m=1;
+h_c=121.4;
+x=0.875;
+disp(x,"(a)the final state at point C is")
+for i=2:6
+alpha(i)=(Hs(i)-hs(i-1))/(Hs(i)-hs(i));
+m=m*alpha(i);    
+end
+disp("kg",m,"(b)The mass of steam raised per kg of steam reaching the condenser is")
+// part(c) thermal efficiency with feed heating
+H_c=2250;
+h_n=hs(6);
+n_th=1-((H_c-h_c)/(m*(H-h_n)));
+hr_t=3600/n_th;
+//(c) the improvement in thermal efficiency and heat rate
+c=H-H_c;
+d=H-h_c;
+n_R=(H-H_c)/(H-h_c);
+hr_R=3600/n_R;
+deln_th=(n_th-n_R)/n_R;
+disp ("%",deln_th*100,"(c)therefore, the improvement in efficiency is")
+delhr_t=(hr_R-hr_t)/hr_R;
+disp ("%",delhr_t*100," and, the improvement in heat rate is")
+
+// part(d) decrease of steam flow to the condenser per kWh due to feed heating
+q_s=m*(H-h_n);
+q_r=H_c-h_c;
+w_t=q_s-q_r;
+wt_m=w_t/m;
+sf_r=3600/wt_m;
+s_c=sf_r/m;
+// without feed heating
+wt_f=H-H_c;
+m_wf=3600/wt_f;
+sr_c=(m_wf-s_c)/m_wf;
+disp ("%",sr_c*100,"(d)the decrease in steam reaching the condenser is")
+disp("comment: the calculation for the improvement in efficiency is wrong in the book.")
+   
diff --git a/2223/CH5/EX5.1/Ex5_1.sav b/2223/CH5/EX5.1/Ex5_1.sav
new file mode 100755
index 000000000..dbc11834b
--- /dev/null
+++ b/2223/CH5/EX5.1/Ex5_1.sav
diff --git a/2223/CH5/EX5.1/Ex5_1.sce b/2223/CH5/EX5.1/Ex5_1.sce
new file mode 100755
index 000000000..5325037be
--- /dev/null
+++ b/2223/CH5/EX5.1/Ex5_1.sce
@@ -0,0 +1,53 @@
+// scilab Code Exa 5.1. Calculation on combined cycle power plant
+
+P_gt=1e5; // Power Output in kW
+m_g=400; // mass flow rate of the exhaust gas in kg/s
+cp_g=1.157; // Specific Heat of gas at Constant Pressure in kJ/(kgK)
+x=0.9; // dryness fraction of steam at the turbine exit
+
+// part(a) Determining capacity of the boiler in kg of steam per hour 
+p1=90; // steam Pressure at the entry of steam turbine in bar
+// from steam tables
+t_6s=303.3; // saturation temperature at 90 bar in degree C
+t_5s=t_6s;
+h_fg=1380.8; // from steam table liquid vapour enthalpy at 90 bar
+pp=20; // pinch point in degree C
+t_6=t_6s+pp;
+h_5s=2744.6;
+h_6s=1363.8;
+
+t4=592.6;  // Exhaust gas temperature at gas turbine end in degree C
+T4=t4+273; // in Kelvin
+p_c=0.1; // Condenser pressure in bar
+t7=176;  // Exhaust gas temperature at stack in degree C
+T7=t7+273; // in Kelvin
+h_7s=191.8; // Specific Enthalpy of water in kJ/kg
+
+m_st=(m_g*cp_g*(t_6-t7))/(h_6s-h_7s);
+disp ("tonnes/hr" ,m_st*3.6,"(a)capacity of the boiler in kg of steam per hour is")
+
+// part(b) temperature of steam at turbine entry
+t_5=t_6+((m_st*(h_5s-h_6s))/(m_g*cp_g)); // energy balance for the evaporator
+
+h_4s=h_5s+(m_g*cp_g*(t4-t_5)/m_st);
+t_4s=540; // in degree C from steam table at p=90 bar
+disp("degree celsius",t_4s,"(b)temperature of steam at turbine entry is")
+
+// part(c)steam turbine plant output and thermal efficiency 
+h_5=2350;
+h_6=2150;
+w_st_s=h_4s-h_5;
+w_st_g=w_st_s*(m_st/m_g);
+P_st=m_st*w_st_s;
+disp("MW",P_st/10e02,"(c)Power output of the steam turbine plant is")
+q_st=h_4s-h_7s;
+n_st=w_st_s/q_st;
+disp ("%" ,n_st*100,"thermal Efficiency of staem turbine plant is")
+
+// part(d) thermal efficiency of the combined cycle plant
+n_gt=0.2666; // Gas turbine plant Efficiency
+w_gt=P_gt/m_g;
+q_gt=w_gt/n_gt;
+n_c=(w_gt+w_st_g)/q_gt;
+disp ("%" ,n_c*100,"(d)thermal Efficiency of combined cycle plant is")
+disp("Comment: Error in Textbook, Answers vary due to Round-off Errors")
diff --git a/2223/CH5/EX5.2/Ex5_2.sav b/2223/CH5/EX5.2/Ex5_2.sav
new file mode 100755
index 000000000..6876cce62
--- /dev/null
+++ b/2223/CH5/EX5.2/Ex5_2.sav
diff --git a/2223/CH5/EX5.2/Ex5_2.sce b/2223/CH5/EX5.2/Ex5_2.sce
new file mode 100755
index 000000000..af901abcb
--- /dev/null
+++ b/2223/CH5/EX5.2/Ex5_2.sce
@@ -0,0 +1,19 @@
+// scilab Code Exa 5.2 combined gas and steam cycle power plant
+P_gt=10e03; // Power Output in kW
+n_st=0.32; // Steam turbine power plant Efficiency
+
+// part(a)steam turbine plant output  
+n_gt=0.2; // Gas turbine plant Efficiency
+q_gt=P_gt/n_gt;
+q_st=(1-n_gt)*q_gt;
+P_st=n_st*q_st;
+disp("MW",P_st/10e02,"(a)Power output of the steam turbine plant is")
+
+// part(b) thermal efficiency of the combined cycle plant
+n_c=n_gt+n_st-(n_gt*n_st);
+disp ("%" ,n_c*100,"(b)thermal Efficiency of combined cycle plant is")
+
+// part(c) the heat rate of the combined cycle plant
+hr_c=3600/n_c; 
+disp ("kJ/kWh",hr_c," (c)Heat Rate of the combined cycle plant is")
+
diff --git a/2223/CH6/EX6.1/Ex6_1.sav b/2223/CH6/EX6.1/Ex6_1.sav
new file mode 100755
index 000000000..d115ee716
--- /dev/null
+++ b/2223/CH6/EX6.1/Ex6_1.sav
diff --git a/2223/CH6/EX6.1/Ex6_1.sce b/2223/CH6/EX6.1/Ex6_1.sce
new file mode 100755
index 000000000..e326be5df
--- /dev/null
+++ b/2223/CH6/EX6.1/Ex6_1.sce
@@ -0,0 +1,18 @@
+// scilab Code Exa 6.1 inward flow radial turbine 32000rpm
+P=150; // Power Output in kW
+N=32e3; // Speed in RPM
+d1=20/100; // outer diameter of the impeller in m
+d2=8/100; // inner diameter of the impeller in m
+V1=387; // Absolute Velocity of gas at entry in m/s
+V2=193; // Absolute Velocity of gas at exit in m/s
+
+// part(a) determining mass flow rate
+u1=%pi*d1*N/60;
+u2=d2*u1/d1;
+w_at=u1^2/10e2;
+m=P/w_at;
+disp ("kg/s" ,m,"(a)mass flow rate is")
+
+// part (b) determining the percentage energy transfer due to the change of radius
+n=((u1^2-u2^2)/2e3)/w_at; 
+disp ("%",n*100,"(b)percentage energy transfer due to the change of radius is")
diff --git a/2223/CH6/EX6.2/Ex6_2.sav b/2223/CH6/EX6.2/Ex6_2.sav
new file mode 100755
index 000000000..7fed43626
--- /dev/null
+++ b/2223/CH6/EX6.2/Ex6_2.sav
diff --git a/2223/CH6/EX6.2/Ex6_2.sce b/2223/CH6/EX6.2/Ex6_2.sce
new file mode 100755
index 000000000..fabe4c998
--- /dev/null
+++ b/2223/CH6/EX6.2/Ex6_2.sce
@@ -0,0 +1,23 @@
+// scilab Code Exa 6.2 radially tipped Centrifugal blower 3000rpm
+P=150; // Power Output in kW
+N=3e3; // Speed in RPM
+d2=40/100; // outer diameter of the impeller in m
+d1=25/100; // inner diameter of the impeller in m
+b=8/100; // impeller width at entry in m
+n_st=0.7; // stage efficiency
+V1=22.67; // Absolute Velocity at entry in m/s
+ro=1.25; // density of air in kg/m3
+
+// part(a) determining the pressure developed
+u2=%pi*d2*N/60;
+u1=d1*u2/d2;
+w_ac=u2^2;
+delh_s=n_st*w_ac;
+delp=ro*delh_s;
+disp ("mm W.G." ,delp/9.81,"(a)the pressure developed is")
+
+// part (b) determining the power required
+A1=%pi*d1*b;
+m=ro*V1*A1;
+P=m*w_ac/10e2;
+disp("kW",P,"(b)Power required is")
diff --git a/2223/CH6/EX6.3/Ex6_3.sav b/2223/CH6/EX6.3/Ex6_3.sav
new file mode 100755
index 000000000..bbefe1ff4
--- /dev/null
+++ b/2223/CH6/EX6.3/Ex6_3.sav
diff --git a/2223/CH6/EX6.3/Ex6_3.sce b/2223/CH6/EX6.3/Ex6_3.sce
new file mode 100755
index 000000000..fa6083404
--- /dev/null
+++ b/2223/CH6/EX6.3/Ex6_3.sce
@@ -0,0 +1,10 @@
+// scilab Code Exa 6.3 Calculation on an axial flow fan
+N=1.47e3; // Speed in RPM
+d=30/100; // Mean diameter of the impeller in m
+ro=1.25; // density of air in kg/m3
+
+// part(b) determining the pressure rise across the fan
+u=%pi*d*N/60;
+w_c=u^2/3;
+delp=ro*w_c;
+disp ("mm W.G." ,delp/9.81,"(b)the pressure rise across the fan is")
diff --git a/2223/CH7/EX7.1/Ex7_1.sav b/2223/CH7/EX7.1/Ex7_1.sav
new file mode 100755
index 000000000..285843cb0
--- /dev/null
+++ b/2223/CH7/EX7.1/Ex7_1.sav
diff --git a/2223/CH7/EX7.1/Ex7_1.sce b/2223/CH7/EX7.1/Ex7_1.sce
new file mode 100755
index 000000000..8aaa4361a
--- /dev/null
+++ b/2223/CH7/EX7.1/Ex7_1.sce
@@ -0,0 +1,45 @@
+// scilab Code Exa 7.1 Calculation for the specific speed
+funcprot(0)
+//part(a)specific speed of gas turbine
+P=2e3; // Gas Turbine Power Output in kW
+N=16e3; // Speed in RPM
+T1=1e3;  // Entry Temperature in Kelvin
+p1=50; //  Entry Pressure in bar
+p2=25; //  Exit Pressure in bar
+cp=1.15e3; // Specific Heat at Constant Pressure in J/(kgK)
+gamma_g=1.3;
+omega=%pi*2*N/60;
+ro=p1*1e5/(((gamma_g-1)/gamma_g)*cp*T1);
+pr=p2/p1; //  pressure ratio
+T2s=T1*(pr^((gamma_g-1)/gamma_g));
+delh_s=cp*(T1-T2s);
+NS=omega*sqrt(P*10e2/ro)*delh_s^(-5/4)
+disp(NS,"(a)the specific speed of gas turbine is")
+
+// part(b)the specific speed of a centrifugal compressor
+pr_b=2; // Compressor pressure ratio
+N_b=24e3; // Speed in RPM
+m=1.5; //  in kg/s
+cp_a=1.005e3; // Specific Heat of air at Constant Pressure in kJ/(kgK)
+R=0.287;
+gamma=1.4;
+T1_b=300;  // Entry Temperature in Kelvin
+p1_b=1; //  Entry Pressure in bar
+ro_b=p1_b*1e2/(R*T1_b);
+omega_b=%pi*2*N_b/60;
+Q=m/ro_b;
+T2=T1_b*(pr_b^((gamma-1)/gamma));
+delh_s_b=cp_a*(T2-T1_b);
+NS_b=omega_b*sqrt(Q)*delh_s_b^(-3/4);
+disp(NS_b,"(b)the specific speed of a centrifugal compressor is")
+
+// part(c)the specific speed of an axial compressor
+pr_c=1.4; // Compressor pressure ratio
+N_c=6e3; // Speed in RPM
+m_c=15; //  in kg/s
+omega_c=%pi*2*N_c/60;
+Q_c=m_c/ro_b;
+T2_c=T1_b*(pr_c^((gamma-1)/gamma));
+delh_s_c=cp_a*(T2_c-T1_b);
+NS_c=omega_c*sqrt(Q_c)*delh_s_c^(-3/4)
+disp(NS_c,"(c)the specific speed of an axial compressor is")
diff --git a/2223/CH7/EX7.2/Ex7_2.sav b/2223/CH7/EX7.2/Ex7_2.sav
new file mode 100755
index 000000000..42652ec8c
--- /dev/null
+++ b/2223/CH7/EX7.2/Ex7_2.sav
diff --git a/2223/CH7/EX7.2/Ex7_2.sce b/2223/CH7/EX7.2/Ex7_2.sce
new file mode 100755
index 000000000..ba50264dc
--- /dev/null
+++ b/2223/CH7/EX7.2/Ex7_2.sce
@@ -0,0 +1,20 @@
+
+// scilab Code Exa 7.2 Calculating the discharge of a geometrically similar blower and specific speed of the fan
+pr=2; // Compressor pressure ratio
+N1=1.47e3; // fan Speed in RPM
+N2=0.36e3; // blower Speed in RPM
+Q1=2; // discharge in m3/s
+h=10e-3; // in m W.G.
+ro_w=10e2;
+ro_a=1.25; // density of air in kg/m3
+omega1=%pi*2*N1/60;
+g=9.81; // in m/s2
+p=ro_w*g*h
+H=p/(ro_a*g);
+delh_s=g*H;
+NS=omega1*sqrt(Q1)*delh_s^(-3/4)
+disp(NS,"the specific speed is")
+// for the same specific speed of two geometrically similar fans
+a=N1/N2;
+Q2=a^2*Q1;
+disp("m3/s",Q2," and the discharge of a geometrically similar blower is")
diff --git a/2223/CH7/EX7.3/Ex7_3.sav b/2223/CH7/EX7.3/Ex7_3.sav
new file mode 100755
index 000000000..aa8ba8af8
--- /dev/null
+++ b/2223/CH7/EX7.3/Ex7_3.sav
diff --git a/2223/CH7/EX7.3/Ex7_3.sce b/2223/CH7/EX7.3/Ex7_3.sce
new file mode 100755
index 000000000..b7d29733d
--- /dev/null
+++ b/2223/CH7/EX7.3/Ex7_3.sce
@@ -0,0 +1,26 @@
+// scilab Code Exa 7.3 Calculation on a small compressor
+pr=1.6; // Compressor pressure ratio
+N1=54e3; // Speed in RPM
+n_c=0.85; // efficiency
+m_a=1.5778; //  in kg/s
+cp_a=1.009; // Specific Heat of air at Constant Pressure in kJ/(kgK)
+gamma=1.4;
+// part (a) determining the power required to drive the compressor
+T01=300;  // Entry Temperature in Kelvin
+p01=1.008; //  Entry Pressure in bar
+n=(gamma-1)/gamma;
+T2s=T01*(pr^n);
+delh_s=cp_a*(T2s-T01)/n_c;
+P=m_a*delh_s;
+disp("kW",P,"(a)Power required to drive the compressor is")
+
+// part (b) determining the speed, mass flow rate, pressure ratio and power required of a geometrically similar compressor
+// geometrically similar compressor of 3 times the size of small compressor is constructed 
+N2=N1/3;
+disp("rpm",N2,"(b)(i)speed of a geometrically similar compressor is")
+m2=9*m_a;
+disp("kg/s",m2,"(b)(ii)mass flow rate of a geometrically similar compressor is")
+disp(pr,"(b)(iii)pressure ratio of a geometrically similar compressor is")
+P2=9*P;
+disp("kW",P2,"(b)(iv)Power required is")
+
diff --git a/2223/CH7/EX7.4/Ex7_4.sav b/2223/CH7/EX7.4/Ex7_4.sav
new file mode 100755
index 000000000..af66304db
--- /dev/null
+++ b/2223/CH7/EX7.4/Ex7_4.sav
diff --git a/2223/CH7/EX7.4/Ex7_4.sce b/2223/CH7/EX7.4/Ex7_4.sce
new file mode 100755
index 000000000..e654fb602
--- /dev/null
+++ b/2223/CH7/EX7.4/Ex7_4.sce
@@ -0,0 +1,35 @@
+// scilab Code Exa 7.4 Calculation on a single stage gas turbine
+
+gamma_g=1.33;
+gamma=1.4
+R_g=284.1;
+R=287;
+P=1e3; // Power Output in kW
+N1=3e3; // Speed in RPM
+n_t=0.87; // efficiency
+cp_g=1.145; // Specific Heat of gas at Constant Pressure in kJ/(kgK)
+cp_a=1.0045; // Specific Heat of air at Constant Pressure in kJ/(kgK)
+
+// part (a)mass flow rate of the gas through the turbine
+T01=1000;  // Entry Temperature in Kelvin
+p01=2.5; //  Entry Pressure in bar
+T01a=500;  // Entry Temperature of air in Kelvin
+p01a=2; //  Entry Pressure of air in bar
+p02=1; //  Exit Pressure in bar
+pr0=p01/p02;
+T02=T01*(pr0^(-((gamma_g-1)/gamma_g)));
+delh_s1=cp_g*(T01-T02)*n_t;
+m_g=P/delh_s1;
+disp("kg/s",m_g,"(a)mass flow rate of the gas through the turbine is")
+
+// part (b)speed, mass flow rate, pressure ratio and power required 
+N2=sqrt(1/2)*5*N1;
+disp("rpm",N2,"(b)(i)speed of a geometrically similar compressor is")
+a=0.2; // a=D2/D1;
+m2=(a^2)*sqrt(R_g/R)*sqrt(T01/T01a)*(p01a/p01)*m_g;
+disp("kg/s",m2,"(b)(ii)mass flow rate of a geometrically similar turbine is")
+delh_s2=0.5*delh_s1;
+P2=m2*delh_s2;
+disp("kW",P2,"(b)(iii)Power developed is")
+pr=(1-(delh_s2/(cp_a*T01a*n_t)))^(-1/((gamma-1)/gamma));
+disp(pr,"(b)(iv)pressure ratio of a geometrically similar turbine is")
diff --git a/2223/CH8/EX8.1/Ex8_1.sav b/2223/CH8/EX8.1/Ex8_1.sav
new file mode 100755
index 000000000..703e8fdcc
--- /dev/null
+++ b/2223/CH8/EX8.1/Ex8_1.sav
diff --git a/2223/CH8/EX8.1/Ex8_1.sce b/2223/CH8/EX8.1/Ex8_1.sce
new file mode 100755
index 000000000..43dd24f30
--- /dev/null
+++ b/2223/CH8/EX8.1/Ex8_1.sce
@@ -0,0 +1,30 @@
+// scilab Code Exa 8.1 Calculation on a compressor cascade
+
+V1=75; // Absolute Velocity of air at entry in m/s
+alpha1=48; // air angle at entry
+alpha2=25; // air angle at exit
+p=1.1; // pitch-chord ratio
+delps=11; // stagnation pressure loss in mm W.G.
+ro=1.25; // density of air in kg/m3
+g=9.81;
+a=0.5*(tand(alpha1)+tand(alpha2)); 
+alpham=atand(a);
+b=0.5*ro*(V1^2);
+Y=delps*g/b;
+disp (Y,"the loss coefficient is")
+c=(cosd(alpham)^3)/(cosd(alpha1)^2);
+C_D=p*Y*c;
+disp (C_D,"the drag coefficient is")
+d=2*p*(tand(alpha1)-tand(alpha2))*cosd(alpham);
+e=C_D*tand(alpham);
+C_L=d-e;
+disp (C_L,"the Lift coefficient is")
+f=(cosd(alpha1)^2)/(cosd(alpha2)^2);
+C_ps=1-f;
+disp (C_ps,"the Ideal pressure recovery coefficient is")
+C_pa=C_ps-Y;
+disp (C_pa,"the Actual pressure recovery coefficient is")
+n_D=C_pa/C_ps;
+disp (n_D,"the Diffuser efficiency is")
+n_dmax=1-(2*C_D/C_L);
+disp (n_dmax,"the Maximum Diffuser efficiency is")
diff --git a/2223/CH8/EX8.2/Ex8_2.sav b/2223/CH8/EX8.2/Ex8_2.sav
new file mode 100755
index 000000000..5d557cc31
--- /dev/null
+++ b/2223/CH8/EX8.2/Ex8_2.sav
diff --git a/2223/CH8/EX8.2/Ex8_2.sce b/2223/CH8/EX8.2/Ex8_2.sce
new file mode 100755
index 000000000..963eb61a0
--- /dev/null
+++ b/2223/CH8/EX8.2/Ex8_2.sce
@@ -0,0 +1,35 @@
+// scilab Code Exa 8.2 Calculation on a turbine blade row cascade
+
+beta1=35; //  blade angle at entry
+beta2=55; // blade angle at exit
+i=5; // incidence
+delta=2.5; // deviation
+alpha1=beta1+i; // air angle at entry
+alpha2=beta2-delta; // air angle at exit
+t_c=0.3; // maximum thickness-chord ratio(t/l)
+a_r=2.5; // aspect ratio
+
+//part(a)optimum pitch-chord ratio from Zweifels relation
+C_z=0.8; // from Zweifel's relation 
+p_c=C_z/(2*(cosd(alpha2)^2)*(tand(alpha1)+tand(alpha2)));
+disp (p_c,"(a)the optimum pitch-chord ratio from Zweifels relation is")
+
+//part(b) loss coefficient from Soderbergs and Hawthorne relations
+ep=alpha1+alpha2; // deflection angle
+Zeeta=0.075;
+b=(1+Zeeta)*(0.975+(0.075/a_r))
+zeeta=b-1;
+disp (zeeta,"(b)(i)the loss coefficient from Soderbergs relation is")
+z_p=0.025*(1+((ep/90)^2)); // Hawthorne's relation
+disp (z_p,"(b)(ii)the loss coefficient from Hawthorne relation is")
+z=(1+(3.2/a_r))*z_p; // the total cascade loss coefficient
+Y=0.5*(z+zeeta); 
+
+// part(c)drag coefficient
+alpham=atand(0.5*(tand(alpha2)-tand(alpha1)));
+C_D=p_c*Y*(cosd(alpham)^3)/(cosd(alpha2)^2);
+disp (C_D,"(c)the drag coefficient is")
+
+// part(d)Lift coefficient
+C_L=(2*p_c*(tand(alpha1)+tand(alpha2))*cosd(alpham))+(C_D*tand(alpham));
+disp (C_L,"(d)the Lift coefficient is")
diff --git a/2223/CH8/EX8.3/Ex8_3.sav b/2223/CH8/EX8.3/Ex8_3.sav
new file mode 100755
index 000000000..0d09cfcec
--- /dev/null
+++ b/2223/CH8/EX8.3/Ex8_3.sav
diff --git a/2223/CH8/EX8.3/Ex8_3.sce b/2223/CH8/EX8.3/Ex8_3.sce
new file mode 100755
index 000000000..b905ea369
--- /dev/null
+++ b/2223/CH8/EX8.3/Ex8_3.sce
@@ -0,0 +1,33 @@
+// scilab Code Exa 8.3 Calculation on a compressor cascade
+theta=25; // Camber angle
+gamma_a=30; // stagger angle
+i=5; // incidence
+t_c=0.031; // momentum thickness-chord ratio(t/l)
+p_c=1; // pitch-chord ratio
+
+//part(a)cascade blade angles
+beta1=((2*gamma_a)+theta)*0.5; //  blade angle at entry
+beta2=((2*gamma_a)-theta)*0.5; // blade angle at exit
+disp ("(a)therefore, the blade angles are")
+disp ("degree",beta1,"beta1=")
+disp ("degree",beta2,"beta2=")
+
+//part(b) the nominal air angles
+alpha1=beta1+i; // air angle at entry
+alpha2=atand(tand(alpha1)-(1.55/(1+(1.5*p_c)))); // air angle at exit
+disp ("(b)therefore, the air angles are")
+disp ("degree",alpha1,"alpha1=")
+disp ("degree",alpha2,"alpha2=")
+
+//part(c) stagnation pressure loss coefficient
+Y=2*t_c*p_c*(cosd(alpha1)^2)/(cosd(alpha2)^3);
+disp (Y,"(c)the stagnation pressure loss coefficient is")
+
+// part(d)drag coefficient
+alpham=atand(0.5*(tand(alpha1)+tand(alpha2)));
+C_D=p_c*Y*(cosd(alpham)^3)/(cosd(alpha1)^2);
+disp (C_D,"(d)the drag coefficient is")
+
+// part(e)Lift coefficient
+C_L=(2*p_c*(tand(alpha1)-tand(alpha2))*cosd(alpham))-(C_D*tand(alpham));
+disp (C_L,"(e)the Lift coefficient is")
diff --git a/2223/CH8/EX8.4/Ex8_4.sav b/2223/CH8/EX8.4/Ex8_4.sav
new file mode 100755
index 000000000..08249f7e6
--- /dev/null
+++ b/2223/CH8/EX8.4/Ex8_4.sav
diff --git a/2223/CH8/EX8.4/Ex8_4.sce b/2223/CH8/EX8.4/Ex8_4.sce
new file mode 100755
index 000000000..e7059d290
--- /dev/null
+++ b/2223/CH8/EX8.4/Ex8_4.sce
@@ -0,0 +1,26 @@
+// scilab Code Exa 8.4 blower type annular cascade tunnel
+
+t=35;
+T=t+273;  // test Temperature in Kelvin
+p=1.02; //  test Pressure in bar
+dm=50/100; // mean diameter of the impeller blade in m
+b=15/100; // blade length in m
+n_o=0.6; // stage efficiency
+R=287;
+c=100; // Maximum Velocity upstream of the cascade in m/s
+ro=p*10e4/(R*T); // density of air in kg/m3
+
+// part(a) determining the total pressure developed by the blower
+d_h=0.5*ro*(c^2);
+loss=0.1*d_h;
+delp=d_h+loss;
+disp ("mm W.G." ,delp/9.81,"(a)the pressure developed is")
+
+// part (b) determining the discharge
+A=%pi*dm*b; // the annulus cross-sectional area 
+Q=c*A;
+disp ("m3/min" ,Q*60,"(b)the discharge is")
+
+// part (c) determining the power required to drive the blower
+P=Q*delp/(n_o*10e2);
+disp("kW",P,"(c)Power required to drive the blower is")
diff --git a/2223/CH8/EX8.5/Ex8_5.sav b/2223/CH8/EX8.5/Ex8_5.sav
new file mode 100755
index 000000000..67fda5ef3
--- /dev/null
+++ b/2223/CH8/EX8.5/Ex8_5.sav
diff --git a/2223/CH8/EX8.5/Ex8_5.sce b/2223/CH8/EX8.5/Ex8_5.sce
new file mode 100755
index 000000000..2dd135a13
--- /dev/null
+++ b/2223/CH8/EX8.5/Ex8_5.sce
@@ -0,0 +1,46 @@
+// scilab Code Exa 8.5 compressor type radial cascade tunnel
+
+M=0.7; // Mach Number
+pr=0.721; // pr=pt/p0 From isentropic gas tables
+t_opt=0.911; // t_opt=Tt/T0
+pa=1.013; //  Atmospheric Pressure in bar
+Ta=306; // in K
+n_c=0.65; // efficiency
+R=288;
+gamma=1.4;
+alpha=30;
+dm=45/100; // mean diameter of the impeller blade in m
+b=10/100; // blade width in m
+cp_a=1.008; // Specific Heat of air at Constant Pressure in kJ/(kgK)
+
+// part(a) pressure ratio of the compressor
+pr_c=1/pr;
+disp(pr_c,"(a)pressure ratio of the compressor is")
+
+// part(b) stagnation pressure in the settling chamber
+p02=pa*pr_c;
+disp("bar",p02,"(b)stagnation pressure in the settling chamber is")
+
+// part(c)test section conditions(static pressure, temperature and velocity)
+n=(gamma-1)/gamma;
+T02s=Ta*(pr_c^((gamma-1)/gamma));
+T02=Ta+((T02s-Ta)/n_c);
+T_t=t_opt*T02;
+p_t=pr*p02;
+c_t=M*sqrt(gamma*R*T_t);
+disp("(c)test section conditions are given by: ")
+disp("bar",p_t,"static pressure of air in the test section is")
+disp("K",T_t,"static temperature of air in the test section is")
+disp("m/s",c_t,"velocity of air in the test section is")
+
+// part(d) determining mass flow rate
+c_r=c_t*sind(alpha);
+ro_t=p_t*1e5/(R*T_t); // density of air in kg/m3
+A_t=%pi*dm*b;
+m=ro_t*A_t*c_r;
+disp("kg/s",m,"(d) mass flow rate of compressor is")
+
+// part (e) determining the power required to drive the air compressor
+delh_s=cp_a*(T02-Ta);
+P=m*delh_s;
+disp("kW",P,"(e)Power required to drive the air compressor is")
diff --git a/2223/CH9/EX9.1/Ex9_1.sav b/2223/CH9/EX9.1/Ex9_1.sav
new file mode 100755
index 000000000..add99dd3d
--- /dev/null
+++ b/2223/CH9/EX9.1/Ex9_1.sav
diff --git a/2223/CH9/EX9.1/Ex9_1.sce b/2223/CH9/EX9.1/Ex9_1.sce
new file mode 100755
index 000000000..09b250600
--- /dev/null
+++ b/2223/CH9/EX9.1/Ex9_1.sce
@@ -0,0 +1,108 @@
+// scilab Code Exa 9.1 Calculation on multi stage turbine
+
+d=1; // mean diameter of the impeller blade in m
+T1=500;  // Initial Temperature in degree C
+t1=T1+273; // in Kelvin
+p1=100; //  Initial Pressure in bar
+N=3e3; // Speed in RPM
+m=100; //  in kg/s
+alpha2=70; // exit angle of the first stage nozzle blades
+
+// part(a) single stage impulse 
+nsti=0.78;
+u=%pi*d*N/60;
+sigma=0.5*(sind(alpha2)); // maximum utilization factor
+c2=u/sigma;
+cx=c2*(cosd(alpha2));
+beta2=atand(0.5*(tand(alpha2))); // beta2=beta3
+wst=2*(u^2)*1e-3;
+P=m*wst;
+disp("(a)for single stage impulse")
+disp("degree",beta2,"blade angles are beta2=beta3= ")
+disp("MW",P*1e-3,"Power developed is")
+
+sv=0.04; // specific volume of steam after expansion in m3/kg
+h=(m*sv)/(cx*%pi*d); // h2=h3=h
+disp("cm",h*1e2,"blade height is")
+delhs=wst/nsti;
+disp("final state of the steam is")
+p=81.5; // from enthalpy-entropy diagram
+T=470;
+disp("bar",p,"p=")
+disp("degree C",T,"T=")
+
+// part(b) Two-stage Curtis wheel  
+nstc=0.65;
+u=%pi*d*N/60;
+sigma2=0.25*(sind(alpha2));
+c2_2=u/sigma2;
+cx2=c2_2*(cosd(alpha2));
+beta2_2=atand((3*u)/cx2); // beta2=beta3
+alpha3=atand((2*u)/(c2_2*cosd(alpha2))); // alpha2'=alpha3
+beta2_s=atand((u)/cx2); // beta2'=beta3'
+wI=6*(u^2)*1e-3;
+wII=2*(u^2)*1e-3;
+wst2=wI+wII;
+P2=m*wst2;
+disp("(b)for Two-stage Curtis wheel")
+disp("degree",alpha3,"air angles are alpha2s=alpha3= ")
+disp("degree",beta2_2,"for first stage blade angles are beta2=beta3= ")
+disp("degree",beta2_s,"for second stage blade angles are beta2s=beta3s= ")
+
+disp("MW",P2*1e-3,"Power developed is")
+
+delhs2=wst2/nstc;
+// from enthalpy-entropy diagram for the expansion
+disp("final state of the steam is")
+p2=27;
+T2=365;
+v2=0.105; // specific volume of steam after expansion in m3/kg
+disp("bar",p2,"p=")
+disp("degree C",T2,"T=")
+disp("m3/kg",v2,"v=")
+h2=(m*v2)/(cx2*%pi*d);
+disp("cm",h2*1e2,"blade height is")
+
+// part(c) Two-stage Reateau wheel  
+nst1=0.78;
+wI3=2*(u^2)*1e-3;
+wII3=2*(u^2)*1e-3;
+wst3=wI3+wII3;
+P3=m*wst3;
+disp("(c)for Two-stage Reateau wheel")
+disp("degree",beta2,"blade angles are beta2=beta3= ")
+disp("MW",P3*1e-3,"Power developed is")
+delhs3=wst3/nst1;
+disp("final state of the steam is")
+p3=65; // from enthalpy-entropy diagram
+T3=445;
+v3=0.05; // specific volume of steam after expansion in m3/kg
+disp("bar",p3,"p=")
+disp("degree C",T3,"T=")
+disp("m3/kg",v3,"v=")
+h3=(m*v3)/(cx*%pi*d);
+disp("cm",h3*1e2,"blade height for the second stage is")
+
+// part(d) single stage 50% reaction 
+nstr=0.85;
+sigma4=sind(alpha2); // maximum utilization factor
+c2_4=u/sigma4; // c2_4=w_3
+cx4=c2_4*(cosd(alpha2)); // alpha2=beta3;
+beta2_4=0; // beta2=alpha3
+wst4=(u^2)*1e-3;
+P4=m*wst4;
+disp("(d)for single stage 50% reaction")
+disp("degree",beta2_4,"blade angles are beta2=alpha3= ")
+disp("degree",alpha2,"and beta3=alpha2= ")
+disp("MW",P4*1e-3,"Power developed is")
+delhs4=wst4/nstr;
+// from enthalpy-entropy diagram 
+disp("final state of the steam is")
+p4=90;
+T4=485;
+v4=0.035;
+disp("bar",p4,"p=")
+disp("degree C",T4,"T=")
+disp("m3/kg",v4,"v=")
+h4=(m*v4)/(cx4*%pi*d);
+disp("cm",h4*1e2,"the rotor blade height at exit is")
diff --git a/2223/CH9/EX9.2/Ex9_2.sav b/2223/CH9/EX9.2/Ex9_2.sav
new file mode 100755
index 000000000..4b8fa4d95
--- /dev/null
+++ b/2223/CH9/EX9.2/Ex9_2.sav
diff --git a/2223/CH9/EX9.2/Ex9_2.sce b/2223/CH9/EX9.2/Ex9_2.sce
new file mode 100755
index 000000000..098438e07
--- /dev/null
+++ b/2223/CH9/EX9.2/Ex9_2.sce
@@ -0,0 +1,93 @@
+// scilab Code Exa 9.2 Calculation on an axial turbine stage 
+
+dh=0.450; // hub diameter in m
+dt=0.750; // tip diameter in m
+d=0.5*(dt+dh); // mean diameter of the impeller blade in m
+r=d/2;
+T1=500;  // Initial Temperature in degree C
+t1=T1+273; // in Kelvin
+p1=100; //  Initial Pressure in bar
+N=6e3; // rotor Speed in RPM
+m=100; //  in kg/s
+alpha2m=75; //  air angle at nozzle exit
+beta2m=45; //  air angle at rotor entry
+beta3m=76; //  air angle at rotor exit
+u=%pi*d*N/60;
+uh=%pi*dh*N/60;
+ut=%pi*dt*N/60;
+// for mean section
+c2m=(cosd(beta2m)/sind(alpha2m-beta2m))*u;
+cx2m=c2m*cosd(alpha2m);
+ct2m=c2m*sind(alpha2m);
+ct3m=(cx2m*tand(beta3m))-u;
+C2=r*ct2m;
+C3=r*ct3m;
+
+// part(a) the relative and absolute air angles 
+disp("for mean section")
+disp("(a) the relative and absolute air angles are")
+disp("degree",beta2m,"air angle at rotor entry is beta2m= ")
+disp("degree",beta3m,"air angle at rotor exit is beta3m= ")
+disp("degree",alpha2m,"air angle at nozzle exit is alpha2m= ")
+// part(b) degree of reaction
+cx=cx2m;
+R=cx*(tand(beta3m)-tand(beta2m))*100/(2*u);
+disp("%",R,"(b)degree of reaction is")
+// part(c) blade-to-gas speed ratio
+sigma=u/c2m;
+disp(sigma,"(c)blade-to-gas speed ratio is")
+// part(d) specific work
+omega=2*%pi*N/60;
+w=omega*(C2+C3);
+disp("kJ/kg",w*1e-3,"(d)specific work is")
+// part(e) the loading coefficient
+z=w/(u^2);
+disp(z,"(e)the loading coefficient is")
+
+// for hub section
+rh=dh/2;
+alpha2h=atand(C2/(rh*cx));
+disp("for hub section")
+disp("(a) the relative and absolute air angles are")
+disp("degree",alpha2h,"air angle at nozzle exit is alpha2h= ")
+beta2h=atand(tand(alpha2h)-(uh/cx));
+disp("degree",beta2h,"air angle at rotor entry is beta2h= ")
+beta3h=atand((C3/(rh*cx))+(uh/cx));
+disp("degree",beta3h,"air angle at rotor exit is beta3h= ")
+// part(b) degree of reaction
+Rh=cx*(tand(beta3h)-tand(beta2h))*100/(2*uh);
+disp("%",Rh,"(b)degree of reaction is")
+// part(c) blade-to-gas speed ratio
+c2h=cx/(cosd(alpha2h));
+sigmah=uh/c2h;
+disp(sigmah,"(c)blade-to-gas speed ratio is")
+// part(d) specific work
+wh=uh*cx*(tand(beta3h)+tand(beta2h));
+disp("kJ/kg",wh*1e-3,"(d)specific work is")
+// part(e) the loading coefficient
+zh=wh/(uh^2);
+disp(zh,"(e)the loading coefficient is")
+
+// for tip section
+rt=dt/2;
+alpha2t=atand(C2/(rt*cx));
+disp("for tip section")
+disp("(a) the relative and absolute air angles are")
+disp("degree",alpha2t,"air angle at nozzle exit is alpha2t= ")
+beta2t=atand(tand(alpha2t)-(ut/cx));
+disp("degree",beta2t,"air angle at rotor entry is beta2t= ")
+beta3t=atand((C3/(rt*cx))+(ut/cx));
+disp("degree",beta3t,"air angle at rotor exit is beta3t= ")
+// part(b) degree of reaction
+Rt=cx*(tand(beta3t)-tand(beta2t))*100/(2*ut);
+disp("%",Rt,"(b)degree of reaction is")
+// part(c) blade-to-gas speed ratio
+c2t=cx/(cosd(alpha2t));
+sigmat=ut/c2t;
+disp(sigmat,"(c)blade-to-gas speed ratio is")
+// part(d) specific work
+wt=ut*cx*(tand(beta3t)+tand(beta2t));
+disp("kJ/kg",wt*1e-3,"(d)specific work is")
+// part(e) the loading coefficient
+zt=wt/(ut^2);
+disp(zt,"(e)the loading coefficient is")
diff --git a/2223/CH9/EX9.3/Ex9_3.sav b/2223/CH9/EX9.3/Ex9_3.sav
new file mode 100755
index 000000000..ecdfda2f5
--- /dev/null
+++ b/2223/CH9/EX9.3/Ex9_3.sav
diff --git a/2223/CH9/EX9.3/Ex9_3.sce b/2223/CH9/EX9.3/Ex9_3.sce
new file mode 100755
index 000000000..1bab42fcf
--- /dev/null
+++ b/2223/CH9/EX9.3/Ex9_3.sce
@@ -0,0 +1,83 @@
+// scilab Code Exa 9.3 Calculation on an axial turbine stage 
+
+dh=0.450; // hub diameter in m
+dt=0.750; // tip diameter in m
+d=0.5*(dt+dh); // mean diameter of the impeller blade in m
+r=d/2;
+R_m=0.5; // degree of reaction for mean section
+T1=500;  // Initial Temperature in degree C
+t1=T1+273; // in Kelvin
+p1=100; //  Initial Pressure in bar
+N=6e3; // rotor Speed in RPM
+m=100; //  in kg/s
+alpha2m=75; //  air angle at nozzle exit
+beta_2m=0; //  air angle at rotor entry
+beta_3m=75; //  air angle at rotor exit
+// assuming radial equillibrium and free vortex flow in the stage, axial velocity is constant throughout
+u_m=%pi*d*N/60;
+uh=%pi*dh*N/60;
+ut=%pi*dt*N/60;
+// for mean section
+c_xm=u_m*cotd(alpha2m);
+c_2m=(1/sind(alpha2m))*u_m;
+c_t2m=u_m;
+
+disp("for mean section")
+// part(c) blade-to-gas speed ratio
+sigma_m=u_m/c_2m;
+disp(sigma_m,"(c)blade-to-gas speed ratio is")
+// part(d) specific work
+w_m=u_m*c_t2m;
+disp("kJ/kg",w_m*1e-3,"(d)specific work is")
+// part(e) the loading coefficient
+shi_m=w_m/(u_m^2);
+disp(shi_m,"(e)the loading coefficient is")
+
+// for hub section
+rh=dh/2;
+n=(sind(alpha2m)^2);
+c_x2h=c_xm*((r/rh)^n);
+c_t2h=c_t2m*((r/rh)^n);
+c_2h=c_2m*((r/rh)^n);
+disp("for hub section")
+disp("(a) the relative air angles are")
+beta2h=atand((c_t2h-uh)/c_x2h);
+disp("degree",beta2h,"air angle at rotor entry is beta2h= ")
+beta3h=atand(uh/c_x2h);
+disp("degree",beta3h,"air angle at rotor exit is beta3h= ")
+// part(b) degree of reaction
+Rh=c_x2h*(tand(beta3h)-tand(beta2h))*100/(2*uh);
+disp("%",Rh,"(b)degree of reaction is")
+// part(c) blade-to-gas speed ratio
+sigmah=uh/c_2h;
+disp(sigmah,"(c)blade-to-gas speed ratio is")
+// part(d) specific work
+wh=uh*c_t2h;
+disp("kJ/kg",wh*1e-3,"(d)specific work is")
+// part(e) the loading coefficient
+shi_h=wh/(uh^2);
+disp(shi_h,"(e)the loading coefficient is")
+
+// for tip section
+rt=dt/2;
+c_x2t=c_xm*((r/rt)^n);
+c_t2t=c_t2m*((r/rt)^n);
+c_2t=c_2m*((r/rt)^n);
+disp("for tip section")
+disp("(a) the relative air angles are")
+beta2t=atand((c_t2t-ut)/c_x2t);
+disp("degree",beta2t,"air angle at rotor entry is beta2t= ")
+beta3t=atand(ut/c_x2t);
+disp("degree",beta3t,"air angle at rotor exit is beta3t= ")
+// part(b) degree of reaction
+Rt=c_x2t*(tand(beta3t)-tand(beta2t))*100/(2*ut);
+disp("%",Rt,"(b)degree of reaction is")
+// part(c) blade-to-gas speed ratio
+sigmat=ut/c_2t;
+disp(sigmat,"(c)blade-to-gas speed ratio is")
+// part(d) specific work
+wt=ut*c_t2t;
+disp("kJ/kg",wt*1e-3,"(d)specific work is")
+// part(e) the loading coefficient
+shi_t=wt/(ut^2);
+disp(shi_t,"(e)the loading coefficient is")
diff --git a/2223/CH9/EX9.4/Ex9_4.sav b/2223/CH9/EX9.4/Ex9_4.sav
new file mode 100755
index 000000000..07ed60ea6
--- /dev/null
+++ b/2223/CH9/EX9.4/Ex9_4.sav
diff --git a/2223/CH9/EX9.4/Ex9_4.sce b/2223/CH9/EX9.4/Ex9_4.sce
new file mode 100755
index 000000000..1ae4688bc
--- /dev/null
+++ b/2223/CH9/EX9.4/Ex9_4.sce
@@ -0,0 +1,32 @@
+// scilab Code Exa 9.4 axial turbine stage 3000 rpm 
+
+d=1; // mean diameter of the impeller blade in m
+r=d/2;
+N=3e3; // rotor Speed in RPM
+a_r(1)=1; // aspect ratio
+a_r(2)=2;
+a_r(3)=3;
+alpha2=70; //  air angle at nozzle exit
+alpha3=0;
+beta_2=54; //  air angle at rotor entry
+sigma=0.5*(sind(alpha2)); // blade to gas speed ratio
+u=%pi*d*N/60;
+c2=u/sigma;
+cx=c2*(cosd(alpha2));
+beta_3=beta_2;  //  air angle at rotor exit
+phi=cx/u;
+e_R=beta_2+beta_3; // Rotor deflection angle
+zeeta_p_N=0.025*(1+((alpha2/90)^2)); // profile loss coefficient for nozzle
+zeeta_p_R=0.025*(1+((e_R/90)^2)); // profile loss coefficient for rotor
+for i=1:3
+disp(a_r(i),"when Aspect ratio=")
+zeeta_N=(1+(3.2/a_r(i)))*zeeta_p_N; // total loss coefficient for nozzle
+zeeta_R=(1+(3.2/a_r(i)))*zeeta_p_R; // total loss coefficient for rotor
+a=(zeeta_R*(secd(beta_3)^2))+(zeeta_N*(secd(alpha2)^2));
+b=phi*(tand(alpha2)+tand(beta_3))-1;
+c=(zeeta_R*(secd(beta_3)^2))+(zeeta_N*(secd(alpha2)^2))+(secd(alpha3)^2);
+n_tt=inv(1+(0.5*(phi^2)*(a/b)));
+disp("%",n_tt*1e2,"total-to-total efficiency is")
+n_ts=inv(1+(0.5*(phi^2)*(c/b)));
+disp("%",n_ts*1e2,"total-to-static efficiency is")
+end
diff --git a/2223/CH9/EX9.5/Ex9_5.sav b/2223/CH9/EX9.5/Ex9_5.sav
new file mode 100755
index 000000000..c051a4df0
--- /dev/null
+++ b/2223/CH9/EX9.5/Ex9_5.sav
diff --git a/2223/CH9/EX9.5/Ex9_5.sce b/2223/CH9/EX9.5/Ex9_5.sce
new file mode 100755
index 000000000..31d0b493d
--- /dev/null
+++ b/2223/CH9/EX9.5/Ex9_5.sce
@@ -0,0 +1,66 @@
+// scilab Code Exa 9.5 Calculation on a gas turbine stage 
+
+Rm=0.5; // Degree of reaction
+funcprot(0);
+T1=1500;  // in Kelvin
+p1=10; //  Initial Pressure in bar
+N=12e3; // rotor Speed in RPM
+m=70; //  in kg/s
+pr=2; // Pressure Ratio
+n_st=0.87; // Stage Efficiency 
+alpha_2=60; //  Fixed Blade exit angle 
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+gamma=1.4;
+n=(gamma-1)/gamma;
+T3ss=T1/(pr^n);
+delh1_3=cp*(T1-T3ss)*n_st;
+delh1_2=0.5*delh1_3;
+c2=sqrt(2*delh1_2);
+sigma_opt=sind(alpha_2);
+u=sigma_opt*c2;
+// part(a) Flow coefficient
+cx=c2*cosd(alpha_2);
+phi=cx/u;
+disp(phi,"(a)Flow coefficient is")
+
+// part(b) mean diameter of the stage
+d=u*60/(%pi*N);
+disp("m",d,"(b)mean diameter of the stage is")
+
+// part(c) power developed
+P=m*delh1_3;
+disp("MW",P*1e-6,"(c)power developed is")
+
+// part(d) pressure ratio across the fixed and rotor blade rings
+delh1_3ss=delh1_3/n_st;
+delT1_3=delh1_3/cp;
+delT1_3ss=delh1_3ss/cp;
+stage_loss=delT1_3ss-delT1_3;
+delT1_2=delh1_2/cp;
+delT1_2s=delT1_2+(0.5*stage_loss)
+pr_stator=((1-(delT1_2s/T1))^(-1/n));
+disp(pr_stator,"(d)pressure ratio across the fixed blade rings is")
+pr_rotor=pr/pr_stator;
+disp(pr_rotor,"and pressure ratio across the rotor blade rings is")
+
+// part(e) hub-tip ratio of the rotor 
+p2=p1/pr_stator;
+T2=T1-delT1_2;
+ro2=(p2*1e5)/(R*T2);
+l2=m/(ro2*cx*%pi*d);
+p3=p2/pr_rotor;
+T3=T1-delT1_3;
+ro3=p3*1e5/(R*T3);
+l3=m/(ro3*cx*%pi*d);
+l=0.5*(l2+l3);
+rm=d/2;
+rh=rm-(l/2);
+rt=rm+(l/2);
+disp(rh/rt,"(e)hub-tip ratio of the rotor is")
+
+// part(f) degree of reaction at the hub and tip
+Rh=1-((1-Rm)*(rm^2/rh^2));
+Rt=1-((1-Rh)*(rh^2/rt^2));
+disp("%",Rh*1e2,"(f)degree of reaction at the hub is")
+disp("%",Rt*1e2,"(f)degree of reaction at the tip is")
author	priyanka	2015-06-24 15:03:17 +0530
committer	priyanka	2015-06-24 15:03:17 +0530
commit	b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b (patch)
tree	ab291cffc65280e58ac82470ba63fbcca7805165 /2223
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