7 files changed, 232 insertions, 0 deletions
diff --git a/1187/CH11/EX11.1/1.sce b/1187/CH11/EX11.1/1.sce
new file mode 100755
index 000000000..da711b045
--- /dev/null
+++ b/1187/CH11/EX11.1/1.sce
@@ -0,0 +1,37 @@
+clc
+
+disp("(a) the density at plane 1")
+
+p1=1.5*10^5; // N/m^2
+R=287; // J/kg.K
+T1=271; // K
+
+rho1=p1/R/T1; 
+disp("Density at plane 1 =")
+disp(rho1)
+disp("kg/m^3")
+
+disp("(b) the stagnation temperature")
+
+u1=270; // m/s
+cp=1005; // J/Kg.K
+
+T0=T1+u1^2/(2*cp);
+disp("The stagnation temperature =")
+disp(T0)
+disp("K")
+
+disp("(c) the temperature and density at plane 2")
+
+u2=320; // m/s
+p2=1.2*10^5; // N/m^2
+
+T2=T0-u2^2/(2*cp);
+disp("Temperature = ")
+disp(T2)
+disp("K")
+
+rho2=p2/(R*T2);
+disp("density =")
+disp(rho2)
+disp("kg/m^3")
diff --git a/1187/CH11/EX11.2/2.sce b/1187/CH11/EX11.2/2.sce
new file mode 100755
index 000000000..e82a3c491
--- /dev/null
+++ b/1187/CH11/EX11.2/2.sce
@@ -0,0 +1,37 @@
+clc
+
+disp("(a) the angle through which the airstream is deflected")
+
+y=1.4;
+R=287; // J/kg.K
+T1=238; // K
+u1=773; // m/s
+beta1=38; // degrees
+cp=1005; // J/kg.K
+
+a1=sqrt(y*R*T1);
+M1=u1/a1;
+
+beta2=atand(tand(beta1)*((2+(y-1)*M1^2*(sind(beta1))^2)/((y+1)*M1^2*(sind(beta1))^2)));
+
+deflection_angle=beta1-beta2;
+disp("Deflection angle =")
+disp(deflection_angle)
+disp("degrees")
+
+disp("(b) the final Mach number")
+
+u2=u1*cosd(beta1)/cosd(beta2);
+
+T2=T1+1/(2*cp)*(u1^2-u2^2);
+a2=sqrt(y*R*T2);
+
+M2=u2/a2;
+
+disp("Final Mach number =")
+disp(M2)
+
+disp("(c) the pressure ratio across the wave.")
+ratio=T2/T1*(tand(beta1)/tand(beta2));
+disp("Pressure ratio =")
+disp(ratio)
+\ No newline at end of file
diff --git a/1187/CH11/EX11.3/3.sce b/1187/CH11/EX11.3/3.sce
new file mode 100755
index 000000000..a17acd6c7
--- /dev/null
+++ b/1187/CH11/EX11.3/3.sce
@@ -0,0 +1,14 @@
+clc
+
+M1=1.8;
+theta1=20.73; // degrees
+theta2=30.73; // degrees
+M2=2.162;
+p1=50; // kPa
+y=1.4;
+
+p2=p1*((1+(y-1)/2*M1^2)/(1+(y-1)/2*M2^2))^(y/(y-1));
+
+disp("Pressure after the bend =")
+disp(p2)
+disp("kPa")
+\ No newline at end of file
diff --git a/1187/CH11/EX11.4/4.sce b/1187/CH11/EX11.4/4.sce
new file mode 100755
index 000000000..63f8adb3e
--- /dev/null
+++ b/1187/CH11/EX11.4/4.sce
@@ -0,0 +1,37 @@
+clc
+
+p=28*10^3; // N/m^2
+y=1.4;
+M1=2.4;
+M2=1;
+T0=291; // K
+R=287; // J/kg.K
+
+disp("(a) the pressures in the reservoir and at the nozzle throat")
+
+p0=p*(1+(y-1)/2*M1^2)^(y/(y-1));
+pc=p0*(1+(y-1)/2*M2^2)^(-y/(y-1));
+
+disp("Pressure in the reservoir =")
+disp(p0)
+disp("N/m^2")
+
+disp("Pressure at the nozzle throat =")
+disp(pc)
+disp("N/m^2")
+
+disp("(b) the temperature and velocity of the air at the exit.")
+
+T=T0*(1+(y-1)/2*M1^2)^(-1);
+
+disp("Temperature =")
+disp(T)
+disp("K")
+
+a=sqrt(y*R*T)
+
+u=M1*a;
+
+disp("Velocity =")
+disp(u)
+disp("m/s")
diff --git a/1187/CH11/EX11.5/5.sce b/1187/CH11/EX11.5/5.sce
new file mode 100755
index 000000000..03c454d26
--- /dev/null
+++ b/1187/CH11/EX11.5/5.sce
@@ -0,0 +1,25 @@
+clc
+
+M_He=1.8;
+y_He=5/3;
+y_air=1.4;
+p2=30; // kPa
+
+// (A/At)=(1+(y-1)/2*M^2)^((y+1)/(y-1))/M^2*(2/(y+1))^((y+1)/(y-1))
+
+//    = (1+1/3*1.8^2)^(4)/1.8^(2)*(3/4)^(4) = 1.828 for helium
+
+//    = (1+0.2*M^2)^6/M^2*1/1.2^6    for air
+// Hence by trial 
+
+M1=1.715;
+disp("Mach number before the shock =")
+disp(M1)
+
+p1=p2/((2*y_air*M1^2-(y_air-1))/(y_air+1));
+
+p0_1=p1*(1+(y_air-1)/2*M1^2)^(y_air/(y_air-1));
+
+disp("Stagnation Pressure =")
+disp(p0_1)
+disp("kPa")
diff --git a/1187/CH11/EX11.6/6.sce b/1187/CH11/EX11.6/6.sce
new file mode 100755
index 000000000..c42e1a6ff
--- /dev/null
+++ b/1187/CH11/EX11.6/6.sce
@@ -0,0 +1,44 @@
+clc
+
+p0=510; // kPa
+pA=500; // kPa
+pB=280; // kPa
+d=0.02; // m
+l_max=12; // m
+
+disp("(a) the value of the friction factor for the pipe")
+
+// At A, pA/p0 = 500/510 = 0.980. From the Isentropic Flow Tables (Appendix 3), M_A = 0.17.
+// From the Fanno Flow Tables (Appendix 3)for M_A = 0.17 and γ = 1.4, pc/pA = 0.1556 and (fl_maxP/A)_A = 21.37
+
+pC=pA*0.1556;
+
+// From the Fanno Tables at pc/pB = 0.278,M_B = 0.302 and (fl_maxP/A)B = 5.21.
+// For a circular pipe P/A=4/d
+M_B=0.302;
+f=(21.37-5.21)/l_max/4*d;
+
+disp("friction factor =")
+disp(f)
+
+disp("(b) the overall length of the pipe, L, if the flow exhausts to atmosphere")
+
+p=100; // kPa
+
+// At exit, pc/p = 77.8/100 = 0.778. From the Fanno Tables, (fl_maxP/A) = 0.07
+L=l_max*(21.37-0.07)/(21.37-5.21);
+
+disp("Overall Length =")
+disp(L)
+disp("m")
+
+disp("(c) the mass flow rate if the reservoir temperature is 294 K.")
+T0=294; // K
+R=287; // J/kg.K
+y=1.4;
+M=0.302;
+
+m=%pi/4*d^2*pB*10^3*M_B*(y*(1+(y-1)*M^2/2)/R/T0)^(1/2);
+disp("mass flow rate =")
+disp(m)
+disp("kg/s")
diff --git a/1187/CH11/EX11.7/7.sce b/1187/CH11/EX11.7/7.sce
new file mode 100755
index 000000000..668052168
--- /dev/null
+++ b/1187/CH11/EX11.7/7.sce
@@ -0,0 +1,38 @@
+clc
+
+p1=8*10^5; // N/m^2
+p2=5*10^5; // N/m^2
+f=0.006;
+l=145; // m
+m=0.32; // kg/s
+R=287; // J/kg.K
+T=288; // K
+y=1.4;
+
+d=(4*f*l*m^2*R*T/(%pi/4)^2/(p1^2-p2^2))^(1/5);
+disp("(a) Diameter of pipe =")
+disp(d)
+disp("m")
+
+rho=p1/R/T;
+A=%pi/4*d^2;
+u=m/rho/A;
+
+a=sqrt(y*R*T);
+
+M1=u/a;
+M2=p1/p2*M1;
+
+disp("(b) Entry and Exit Mach number =")
+
+disp("Entry Mach number =")
+disp(M1)
+
+disp("Exit Mach number =")
+disp(M2)
+
+disp("(c) Determine the pressure halfway along the pipe.")
+px=sqrt((p1^2+p2^2)/2);
+disp("Pressure =")
+disp(px)
+disp("N/m^2")
+\ No newline at end of file