1 files changed, 33 insertions, 0 deletions
diff --git a/167/CH17/EX17.9/ex9.sce b/167/CH17/EX17.9/ex9.sce
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+++ b/167/CH17/EX17.9/ex9.sce
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+//ex9
+//Shock Wave in a Converging–Diverging Nozzle
+clear
+clc
+//fluid property at exi nozzle
+P01=1;//pressure in MPa
+P1=0.1278;//pressure in MPa
+T1=444.5;//temperature in K
+d1=1.002;//density in Kg/m^3
+//The fluid properties after the shock (denoted by subscript 2) are related to those before the shock through the functions listed in Table A–33
+Ma1=2;
+Ma2=0.5774;
+P02=0.7209*P01;//stagnation pressure in MPa
+P2=4.5*P1;//Static Pressure in MPa
+T2=1.6875*T1;//Static Pressure in K
+d2=2.6667*d1;//Static Pressure n kg/m^3
+
+printf('(a) Stagnation pressure = %.0f MPa \n',P02);
+printf('     Static PRessure = %.4f MPa \n',P2);
+printf('     Static Temperature = %.1f K \n',T2);
+printf('     static density = %.2f kg/m^3 \n',d2);
+//(b)
+R=0.287;
+Cp=1.005;//specific heat at constant pressure in kJ/kg.K
+S=Cp*log(T2/T1)-R*log(P2/P1);//entropy change in kJ/kg.K
+printf(' (b) The entropy change across the shock = %.4f kJ/kg.K \n',S);
+//(c)
+k=1.4;
+V2=Ma2*sqrt(k*R*T2*1000);
+printf(' (c) Air velocity,V2 = %.0f m/s \n',V2);
+ms=2.86;//same as previous example 
+printf(' (d) Mass Flow rate  = %.2f kg/sec \n',ms);
+