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+//Example 12_15
+clc;clear;
+//Properties
+k=1.4;
+C_p=1.005;// kJ/kg*K
+R=0.287;// kJ/kg*K
+// given values
+D=0.15;// m
+V_1=80;// m/s
+T_1=550;// K
+P_1=480;// kPa
+HV=42000;// kJ/kg
+AF=40;
+
+//Calculation
+rho_1=P_1/(R*T_1);// kg/m^3
+A=%pi*D^2*V_1;// m^2
+m_air=rho_1*A*V_1; // kg/s
+m_f=m_air/AF;// kg/s
+Q=m_f*HV;// kW
+q=Q/m_air;// kJ/kg
+T_01=T_1+(V_1^2/(2*C_p*1000));// K
+c_1=sqrt(k*R*T_1); // m/s
+Ma_1=V_1/c_1;
+T_02=+(q+C_p);// K
+// From Table A-15
+T_c=T_01/0.1291;// K
+T_c1=T_02/T_c;
+//Using T_c1 value & From Table A-15
+Ma_2=0.3142;
+printf('The exit Mach number ,Ma_2=%0.4f \n',Ma_2);
+T_2=2.848*T_1;// K
+printf('The exit temperature,T_2=%0.0f K\n',T_2);
+P_2=0.9142*P_1;// kPa
+printf('The exit pressure ,P_2=%0.0f kPa\n',P_2);
+V_2=3.117*V_1;// m/s
+printf('The exit velocity ,V_2=%0.0f m/s\n',V_2);