initial commit / add all books

13 files changed, 447 insertions, 0 deletions

diff --git a/2870/CH17/EX17.1/Ex17_1.sce b/2870/CH17/EX17.1/Ex17_1.sce
new file mode 100755
index 000000000..be542d830
--- /dev/null
+++ b/2870/CH17/EX17.1/Ex17_1.sce
@@ -0,0 +1,22 @@
+clc;clear;

+//Example 17.1

+

+//given data

+V1=250;

+T1=255.07;

+P1=54.05;

+h=5000;

+

+//from Table A-2a

+cp=1.005;//in kJ/kg-K

+k=1.4;

+

+//calculations

+T01=T1+V1^2/(2*cp*1000);//factor of 1000 to convert kJ to J

+P01=P1*(T01/T1)^(k/(k-1));

+//given pressure ratio in compressor *

+// T02 = T01*(P02/P01)^((k-1)/k)

+T02 = T01*(8)^((k-1)/k);

+win=cp*(T02-T01);

+disp(P01,'the stagnation pressure at the compressor inlet in kPa');

+disp(win,'the required compressor work per unit mass in kJ/kg')

diff --git a/2870/CH17/EX17.10/Ex17_10.sce b/2870/CH17/EX17.10/Ex17_10.sce
new file mode 100755
index 000000000..e7de46e5f
--- /dev/null
+++ b/2870/CH17/EX17.10/Ex17_10.sce
@@ -0,0 +1,12 @@
+clc;clear;

+//Example 17.10

+

+//given data

+//using protactor frpm Fig 17-36

+u=19;//u stands for angle of the mach lines

+

+//calculations

+//by Eq. 17-47

+//i.e u= asin(1/Ma)

+Ma=1/sind(u);

+disp(Ma,'The Mach number is')

diff --git a/2870/CH17/EX17.11/Ex17_11.sce b/2870/CH17/EX17.11/Ex17_11.sce
new file mode 100755
index 000000000..d3585e02c
--- /dev/null
+++ b/2870/CH17/EX17.11/Ex17_11.sce
@@ -0,0 +1,37 @@
+clc;clear;

+//Example 17.11

+

+//given data

+Ma1=2;

+P1=75;

+O=10;//angle b/w shock wave and normal

+

+//constants used

+k=1.4;

+

+//calcualtions

+//with given values of Ma1 and O from Eq 17-46

+Bweak=39.3;

+Bstrong=83.7;

+//Weak shock

+Ma1w=Ma1*sind(Bweak);

+//Strong shock

+Ma1s=Ma1*sind(Bstrong);

+//from second part Eq 17-40

+Ma2w=0.8032;

+Ma2s=0.5794;

+//pressure ratio = (2*k*Ma^2 - k + 1)/(k + 1 )

+//Weak shock

+P2w=P1*(2*k*Ma1w^2 - k + 1)/(k + 1 );

+P2w=ceil(P2w);

+disp(P2w,'pressure for weak shock in kPa');

+//Strong shock

+P2s=P1*(2*k*Ma1s^2 - k + 1)/(k + 1 );

+P2s=floor(P2s);

+disp(P2s,'pressure for strong shock in kPa');

+//Weak shock

+Ma2=Ma2w/sind(Bweak-O);

+disp(Ma2,'Mach number downstream for weak shock');

+//Strong shock

+Ma2=Ma2s/sind(Bstrong-O);

+disp(Ma2,'Mach number downstream for strong shock');

diff --git a/2870/CH17/EX17.12/Ex17_12.sce b/2870/CH17/EX17.12/Ex17_12.sce
new file mode 100755
index 000000000..9807e4715
--- /dev/null
+++ b/2870/CH17/EX17.12/Ex17_12.sce
@@ -0,0 +1,23 @@
+clc;clear;

+//Example 17.12

+

+//given data

+Ma1=2;

+P1=230;

+O=10;//O stands for angle of the mach lines

+

+//constants used

+k=1.4;

+

+//calculations

+//Eq. 17–49 for the upstream Prandtl–Meyer function

+vMa1=sqrt((k+1)/(k-1))*atand(sqrt((k-1)*(Ma1^2-1)/(k+1)))-atand(sqrt(Ma1^2-1));

+//Eq. 17–48 to calculate the downstream Prandtl–Meyer function

+vMa2=O+vMa1;

+//using equation solver as implict nature of Eq 17-49

+Ma2=2.385;

+disp(Ma2,'downstream Mach number Ma2 is');

+//P2 = (P2/P0)/(P1/P0) * P1

+P2= (1 + (k-1)*Ma2^2/2 )^(-k/(k-1)) / (1 + (k-1)*Ma1^2/2 )^(-k/(k-1)) * P1;

+P2=floor(P2);

+disp(P2,'downstream pressure in kPa')

diff --git a/2870/CH17/EX17.15/Ex17_15.sce b/2870/CH17/EX17.15/Ex17_15.sce
new file mode 100755
index 000000000..a52aa1b13
--- /dev/null
+++ b/2870/CH17/EX17.15/Ex17_15.sce
@@ -0,0 +1,55 @@
+clc;clear;

+//Example 17.15

+

+//given data

+P1=480;

+T1=550;

+V1=80;

+d1=15/100;//diameter in m

+AF=40;//air to fuel ratio

+HV=40000;//heating value in kJ/kg

+

+//from Table A-2a

+R=0.287;//in kJ/kg-K

+cp=1.005;//in kJ/kg-K

+k=1.4;

+

+//calculations

+p1=P1/(R*T1);

+A1=%pi*d1^2/4;

+mair=p1*A1*V1;

+mfuel=mair/AF;

+Q=mfuel*HV;

+q=Q/mair;

+T01=T1+V1^2/(2*cp);

+c1=sqrt(k*R*T1*1000);//factor of 1000 to convert kJ to J

+Ma1=V1/c1;

+//exit stagnation energy equation q= Cp (T02 - T01)

+T02=T01+q/cp;

+//from Table A–34

+//at Ma1

+//s stands for * symbol

+T0s=0.1291;//T0/Ts

+Ts0=T01/T0s;

+T2s=T02/Ts0;//T02/T*0

+//from Table A–34 at this ratio

+Ma2=0.3142;

+//Rayleigh flow relations corresponding to the inlet and exit Mach no

+//at Ma1

+T1s=0.1541;//T1/Ts

+P1s=2.3065;//P1/Ps

+V1s=0.0668;//V1/Vs

+//at Ma2

+T2s=0.4389;//T2/Ts

+P2s=2.1086;//P2/Ps

+V2s=0.2082;//V2/Vs

+T2=T2s/T1s*T1;

+T2=floor(T2);

+P2=P2s/P1s*P1;

+P2=ceil(P2);

+V2=V2s/V1s*V1;

+V2=floor(V2);    

+disp(Ma2,'Mach Number at exit');

+disp(T2,'Temperature in K');

+disp(P2,'Pressure in kPa');

+disp(V2,'Velocity in m/s')

diff --git a/2870/CH17/EX17.16/Ex17_16.sce b/2870/CH17/EX17.16/Ex17_16.sce
new file mode 100755
index 000000000..b868f27ff
--- /dev/null
+++ b/2870/CH17/EX17.16/Ex17_16.sce
@@ -0,0 +1,52 @@
+clc;clear;

+//Example 17.16

+

+//given data

+P01=2*1000;//factor of 1000 to convert MPa to kPa

+T1=400;

+V1=0;//negligible

+nN=0.93;

+m=2.5;

+P2=300;

+

+//calculations

+

+//part - a

+P201=P2/P01;

+//critical pressure ratio at this values is 0.546

+Pt=0.546*P01;

+//at inlet

+h1=3248.4;

+h01=h1;

+s1=7.1292;

+//at throat

+st=s1;

+ht=3076.8;

+vt=0.24196;

+Vt=sqrt(2*(h01-ht)*1000);//factor of 1000 to convert kJ to J

+At=m*vt/Vt;

+//at state 2s

+s2s=s1;

+h2s=2783.6;

+//nN = (h01 - h2)/ (h01 - h2s)

+h2=h01-nN*(h01-h2s);

+//at P2 and h2

+v2=0.67723;

+s2=7.2019;

+V2=sqrt(2*(h01-h2)*1000);//factor of 1000 to convert kJ to J

+A2=m*v2/V2;

+disp((At*10000),'throat area in cm^2');

+disp((A2*10000),'exit area in cm^2');

+

+//part - b

+// at st=7.1292

+//pressures of 1.115 and 1.065 MPa

+//c calculated using tables

+c=sqrt((1115-1065)/(1/0.23776 - 1/0.24633)*1000);//factor of 1000 to convert kPa to Pa

+Ma=Vt/c;

+disp(Ma,'the Mach number at the throat');

+// at s2=7.2019

+//pressures of 325 and 275 kPa

+c=sqrt((325-276)/(1/0.63596 - 1/0.72245)*1000);//factor of 1000 to convert kPa to Pa

+Ma=V2/c;

+disp(Ma,'the Mach number at the nozzle exit')

diff --git a/2870/CH17/EX17.2/Ex17_2.sce b/2870/CH17/EX17.2/Ex17_2.sce
new file mode 100755
index 000000000..adb616759
--- /dev/null
+++ b/2870/CH17/EX17.2/Ex17_2.sce
@@ -0,0 +1,17 @@
+clc;clear;

+//Example 17.2

+

+//given data

+V=200;

+T=30+273;//converted in K

+

+//from Table A-2a

+R=0.287;//in kJ/kg-K

+k=1.4;

+

+//calculations

+c=sqrt(k*R*T*1000);//factor of 1000 to convert kJ to J

+c=ceil(c);

+disp(c,'the speed of sound in m/s');

+Ma=V/c;

+disp(Ma,'the Mach number at the diffuser inlet')

diff --git a/2870/CH17/EX17.3/Ex17_3.sce b/2870/CH17/EX17.3/Ex17_3.sce
new file mode 100755
index 000000000..3bcbe259d
--- /dev/null
+++ b/2870/CH17/EX17.3/Ex17_3.sce
@@ -0,0 +1,26 @@
+clc;clear;

+//Example 17.3

+

+//given data

+T0=200+273;//converted in K

+P0=1400;

+//stagnant temp. & pressure is same as inlet due to small inlet velocity

+P=1200;

+m=3;

+

+//from Table A-2a

+cp=0.846;//in kJ/kg-K

+R=0.1889;//in kJ/kg-K

+k=1.289;

+

+//calculations

+T=T0*(P/P0)^((k-1)/k);

+V=sqrt(2*cp*(T0-T)*1000);//factor of 1000 to convert kJ to J

+p=P/(R*T);

+A=m/(p*V);

+c=sqrt(k*R*T*1000);//factor of 1000 to convert kJ to J

+Ma=V/c;

+disp(V,'velocity in m/s');

+disp(p,'density in kg/m^3');

+disp((A*10000),'flow area in cm^2');

+disp(Ma,'Mach number');

diff --git a/2870/CH17/EX17.4/Ex17_4.sce b/2870/CH17/EX17.4/Ex17_4.sce
new file mode 100755
index 000000000..b79795a73
--- /dev/null
+++ b/2870/CH17/EX17.4/Ex17_4.sce
@@ -0,0 +1,21 @@
+clc;clear;

+//Example 17.4

+

+//given data

+T0=200+273;//converted in K

+P0=1400;

+

+//from Table A-2a

+k=1.289;

+

+//calculations

+//Tc & Tr stands for critical temp and ratio respectively

+//Pc & Pr stands for critical temp and ratio respectively

+Tr=2/(k+1);

+Pr=(2/(k+1))^(k/(k-1));

+Tc=Tr*T0;

+Pc=Pr*P0;

+Tc=floor(Tc);

+Pc=ceil(Pc);

+disp(Tc,'critical temperature in K');

+disp(Pc,'critical pressure on kPa')

diff --git a/2870/CH17/EX17.5/Ex17_5.sce b/2870/CH17/EX17.5/Ex17_5.sce
new file mode 100755
index 000000000..a5b9c1738
--- /dev/null
+++ b/2870/CH17/EX17.5/Ex17_5.sce
@@ -0,0 +1,47 @@
+clc;clear;

+//Example 17.5

+

+//given data

+Vi=150;

+Ti=600+273;

+Pi=1;

+At=50/10000;//converted into m^2

+

+//from Table A-2a

+R=0.287;//in kJ/kg-K

+cp=1.005;//in kJ/kg-K

+k=1.4;

+

+//calculations

+Toi=Ti+Vi^2/(2*cp*1000);//factor of 1000 to convert kJ to J

+Poi=Pi*(Toi/Ti)^(k/(k-1));

+//flow is isentropic 

+//stagnation temp. and pressure values remain constant

+To=Toi;

+Po=Poi;

+//from Table 17–2

+//The critical-pressure ratio is 0.5283

+

+//Part a

+Pb=0.7;

+Pca=Pb/Po;

+// Pca > 0.5283

+//exit plane pressure is equal to the back pressure

+Pt=Pb;

+//from Table A–32

+Mat=0.778;

+//Tt/To = 0.892

+Tt=0.892*To;

+pt=Pt*1000/(R*Tt);//factor of 1000 to convert MPa to kPa

+Vt=Mat*sqrt(k*R*Tt*1000);//factor of 1000 to convert kJ to J

+ma=pt*At*Vt;

+disp(ma,'the mass flow rate through the nozzle when the back pressure is 0.7 MPa in kg/s');

+

+//Part b

+Pb=0.4;

+Pca=Pb/Po;

+// Pca < 0.5283

+//sonic conditions exists at the exit

+Ma=1;

+mb=At*(Po*1000)*(sqrt(k*1000/(R*To)))*(2/(k+1))^((k+1)/(2*(k-1)));//factor of 1000 to convert MPa to kPa and kJ to J

+disp(mb,'the mass flow rate through the nozzle when the back pressure is 0.4 MPa in kg/s');

diff --git a/2870/CH17/EX17.6/Ex17_6.sce b/2870/CH17/EX17.6/Ex17_6.sce
new file mode 100755
index 000000000..3d96d25c0
--- /dev/null
+++ b/2870/CH17/EX17.6/Ex17_6.sce
@@ -0,0 +1,31 @@
+clc;clear;

+//Example 17.6

+

+//given data

+T1=400;

+P1=100;

+Ma1=0.3;

+A21=0.8;//A2/A1

+

+//assumption

+k=1.4;

+

+//from Table A–32

+//at Ma1=0.3

+//s stands for * symbol

+A1s = 2.0351;//A1/As

+T10 = 0.9823;//T1/T0

+P10 = 0.9305;//P1/P0

+A2s = A21*A1s;//A2/As

+//at this value of A2/As

+T20=0.9701;//T2/T0

+P20=0.8993;//P2/P0

+Ma2=0.391;

+

+//calculations

+T2=T1*T20/T10;

+T2=floor(T2);

+P2=P1*P20/P10;

+disp(Ma2,'Ma2 is ');

+disp(T2,'T2 in K is');

+disp(P2,'P2 in kPa is')

diff --git a/2870/CH17/EX17.7/Ex17_7.sce b/2870/CH17/EX17.7/Ex17_7.sce
new file mode 100755
index 000000000..71a049ec0
--- /dev/null
+++ b/2870/CH17/EX17.7/Ex17_7.sce
@@ -0,0 +1,58 @@
+clc;clear;

+//Example 17.7

+

+//given data 

+T0=800;

+P0=1;

+Vi=0;//negligible 

+At=20;

+Mae=2

+

+//from Table A-2a

+R=0.287;//in kJ/kg-K

+k=1.4;

+

+//calculations

+

+//part - a

+// Mach no. at exit is 2 hence sonic conditions at throat

+p0=P0*1000/(R*T0);//factor of 1000 to convert MPa to kPa

+//from Table A-32 at Mat=1

+//s stands for * symbol

+Ps0 = 0.5283;//Ts/T0

+Ts0 = 0.8333;//Ps/P0

+ps0=0.6339;//ps/p0

+Ps=Ps0*P0;

+Ts=Ts0*T0;

+ps=ps0*p0;

+As=At;

+Vs=sqrt(k*R*Ts*1000);//factor of 1000 to convert kJ to J

+disp('the throat conditions');

+disp(Ps,'Presssure in MPa');

+disp(Ts,'Temperature in K');

+disp(ps,'density in kg/m^3');

+disp(As,'area in cm^2');

+disp(Vs,'velocity in m/s');

+

+//part - b

+//from Table A-32

+//at Mae=2

+Te0 = 0.5556;//Te/T0

+Pe0 = 0.1278;//Pe/P0

+pe0= 0.2300;//pe/p0

+Ae0= 1.6875;//Ae/Ao

+Pe=Pe0*P0;

+Te=Te0*T0;

+pe=pe0*p0;

+Ae=Ae0*At;

+Ve=Mae*sqrt(k*R*Te*1000);//factor of 1000 to convert kJ to J

+disp('the exit plane conditions, including the exit area');

+disp(Pe,'Presssure in MPa');

+disp(Te,'Temperature in K');

+disp(pe,'density in kg/m^3');

+disp(Ae,'area in cm^2');

+disp(Ve,'velocity in m/s');

+

+//part - c

+m=ps*As*Vs/10000;//factor of 10000 to convert cm^2 to m^2

+disp(m,'the mass flow rate through the nozzle in kg/s');

diff --git a/2870/CH17/EX17.9/Ex17_9.sce b/2870/CH17/EX17.9/Ex17_9.sce
new file mode 100755
index 000000000..28e3da2c2
--- /dev/null
+++ b/2870/CH17/EX17.9/Ex17_9.sce
@@ -0,0 +1,46 @@
+clc;clear;

+//Example 17.9

+

+//given data

+m=2.86;

+Ma1=2;

+P01=1;

+P1=0.1278;

+T1=444.5;

+p1=1.002;

+

+//from Table A-2a

+R=0.287;//in kJ/kg-K

+cp=1.005;//in kJ/kg-K

+k=1.4;

+

+//calculations

+

+//part - a

+//from Table A-33 at Ma1=2.0

+Ma2=0.5774;

+P0201=0.7209;//P02/P01

+P21=4.5;//P2/P1;

+T21=1.6875;//T2/T1

+p21=2.6667;//p2/p1

+P02=P0201*P01;

+P2=P21*P1;

+T2=T21*T1;

+p2=p21*p1;

+disp(P02,'the stagnation pressure in MPa');

+disp(P2,'the static pressure in MPa');

+disp(T2,'static temperature in K');

+disp(p2,'static density in kg/m^3');

+

+//part - b

+//s21 = s2 - s1

+s21=cp*log(T2/T1)-R*log(P2/P1);

+disp(s21,'the entropy change across the shock in kJ/kg-K');

+

+//part - c

+V2=Ma2*sqrt(k*R*T2*1000);//factor of 1000 to convert kJ to J

+V2=ceil(V2);

+disp(V2,'the exit velocity in m/s');

+

+//part - d

+disp('flow rate is not affected by presence of shock waves amd remains 2.86 kg/sec')