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