initial commit / add all books

6 files changed, 116 insertions, 0 deletions

diff --git a/172/CH17/EX17.1/ex1.sce b/172/CH17/EX17.1/ex1.sce
new file mode 100755
index 000000000..81693cafc
--- /dev/null
+++ b/172/CH17/EX17.1/ex1.sce
@@ -0,0 +1,13 @@
+//ques1

+//to determine isentropic stagnation pressure and temperature 

+clear

+clc

+T=300;//Temperature of air in K

+P=150;//Pressure of air in kPa

+v=200;//velocity of air flow n m/s

+Cp=1.004;//specific heat at constant pressure in kJ/kg

+To=v^2/(2000*Cp)+T;//stagnation temperature in K

+k=1.4;//constant

+Po=P*(To/T)^(k/(k-1));//stagnation pressure in kPa

+printf('Stagnation Temperature = %.1f K \n',To);

+printf(' Stagnation Pressure = %.1f kPa \n',Po);
\ No newline at end of file
diff --git a/172/CH17/EX17.3/ex3.sce b/172/CH17/EX17.3/ex3.sce
new file mode 100755
index 000000000..c55647364
--- /dev/null
+++ b/172/CH17/EX17.3/ex3.sce
@@ -0,0 +1,18 @@
+//ques3

+//determining the thrust acting on a control surface

+clear

+clc

+//i-inlet

+//e-exit

+//using momentum equation on control surface in x direction

+me=20.4;//mass exiting in kg

+mi=20;//mass entering in kg

+ve=450;//exit velocity in m/s

+vi=100;//exit velocity in m/s

+Pi=95;//Pressure at inlet in kPa

+Pe=125;//Pressure at exit in kPa

+Po=100;//surrounding pressure in kPa

+Ai=0.2;//inlet area in m^2

+Ae=0.1;//exit area in m^2

+Rx=(me*ve-mi*vi)/1000-(Pi-Po)*Ai+(Pe-Po)*Ae;//thrust in x direction in kN

+printf('Thrust acting in x direction = %.2f kN',Rx); 
\ No newline at end of file
diff --git a/172/CH17/EX17.5/ex5.sce b/172/CH17/EX17.5/ex5.sce
new file mode 100755
index 000000000..d655a00f7
--- /dev/null
+++ b/172/CH17/EX17.5/ex5.sce
@@ -0,0 +1,13 @@
+//ques5

+//determining velocity of sound in air

+clear

+clc

+k=1.4;//constant

+R=0.287;//gas constant

+//at 300K

+T1=300;//K

+c1=sqrt(k*R*T1*1000);

+printf('Speed of sound at %.0f K = %.1f m/s \n',T1,c1);

+T2=1000;//K

+c2=sqrt(k*R*T2*1000);

+printf(' Speed of sound at %.0f K = %.1f m/s \n',T2,c2);
\ No newline at end of file
diff --git a/172/CH17/EX17.6/ex6.sce b/172/CH17/EX17.6/ex6.sce
new file mode 100755
index 000000000..b1b91e1c4
--- /dev/null
+++ b/172/CH17/EX17.6/ex6.sce
@@ -0,0 +1,23 @@
+//ques6

+//determining mass flow rate through control volume

+clear

+clc

+k=1.4;//constant

+R=0.287;//gas constant

+To=360;//stagnation Temperature in K 

+T=To*0.8333;//Temperature of air in K, 0.8333 stagnation ratio from table

+v=sqrt(k*R*T*1000);//velocity in m/s

+P=528;//stagnation pressure in kPa

+d=P/(R*T);//stagnation density in kg/m^3

+A=500*10^-6;//area in m^2

+ms=d*A*v;//mass flow rate in kg/s

+printf('Mass flow rate at the throat section = %.4f kg/s \n',ms);

+//e-exit state

+Te=To*0.9381;//exit temperature in K, ratio from table

+ce=sqrt(k*R*Te*1000);//exit velocity of sound in m/s

+Me=0.573;//Mach number

+ve=Me*ce;

+Pe=800;//exit pressure in kPa

+de=Pe/R/Te;

+mse=de*A*ve;

+printf(' Mass flow rate at the exit section = %.4f kg/s \n',mse);
\ No newline at end of file
diff --git a/172/CH17/EX17.7/ex7.sce b/172/CH17/EX17.7/ex7.sce
new file mode 100755
index 000000000..37ad710db
--- /dev/null
+++ b/172/CH17/EX17.7/ex7.sce
@@ -0,0 +1,31 @@
+//ques7

+//determining exit properties in a control volume

+clear

+clc

+Po=1000;//stagnation pressure in kPa

+To=360;//stagnation temperature in K

+

+//when diverging section acting as nozzle

+Pe1=0.0939*Po;//exit pressure of air in kPa

+Te1=0.5089*To;//exit temperature in K

+k=1.4;//constant

+R=0.287;//gas constant for air

+ce=sqrt(k*R*Te1*1000);//velocity of sound in exit section in m/s

+Me=2.197;//mach number from table

+ve1=Me*ce;//velocity of air at exit section in m/s

+disp(" When diverging section act as a nozzle :-");

+printf('Exit pressure  = %.1f kPa \n',Pe1);

+printf('Exit Temperature = %.1f K \n',Te1);

+printf('Exit velocity = %.1f m/s \n',ve1);

+

+//when diverging section act as diffuser

+Me=0.308;

+Pe2=0.0936*Po;//exit pressure of air in kPa

+Te2=0.9812*To;//exit temperature in K

+ce=sqrt(k*R*Te2*1000);//velocity of sound in exit section in m/s

+ve2=Me*ce;

+disp(" When diverging section act as a diffuser :-");

+printf('Exit pressure  = %.1f kPa \n',Pe2);

+printf('Exit Temperature = %.1f K \n',Te2);

+printf('Exit velocity = %.1f m/s \n',ve2);

+

diff --git a/172/CH17/EX17.9/ex9.sce b/172/CH17/EX17.9/ex9.sce
new file mode 100755
index 000000000..4da76a754
--- /dev/null
+++ b/172/CH17/EX17.9/ex9.sce
@@ -0,0 +1,18 @@
+//ques9

+//determining exit plane properties in control volume

+clear

+clc

+//x-inlet

+//y-exit

+Mx=1.5;//mach number for inlet

+My=0.7011;//mach number for exit

+Px=272.4;//inlet pressure in kPa

+Tx=248.3;//inlet temperature in K

+Pox=1000;//stagnation pressure for inlet

+Py=2.4583*Px;//Exit Pressure in kPa

+Ty=1.320*Tx;//Exit temperature in K

+Poy=0.9298*Pox;//Exit pressure in kPa

+

+printf('Exit pressure = %.1f kPa \n',Py);

+printf(' Exit temperature = %.1f K \n',Ty);

+printf(' Exit stagnation pressure = %.1f kPa \n',Poy);
\ No newline at end of file