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+// Example 12_7
+clc;clear;funcprot(0);
+//Given values
+P_0=1000;// kPa;
+T_0=800;// K
+k=1.4;//The specific heat ratio of air 
+Ma_2=2;// Exit Mach number
+a=20;// Throat area in cm^2
+//Properties
+R=0.287;// kJ/kg.k
+
+// Calculation
+rho_0=P_0/(R*T_0);// kg/m^3
+P_0=1;// MPa
+//(a)At the throat of the nozzle Ma=1, and from Table A–13 
+//P*=P_c;T*=T_c;rho*=rho_c;V*=V_c;c*=c_c;
+P_c=0.5283*P_0;// MPa
+printf('(a)The throat conditions,P*=%0.4f MPa\n',P_c);
+T_c=0.8333*T_0;// K
+printf('                          T*=%0.1f K\n',T_c);
+rho_c=0.6339*rho_0;// kg/m^3
+printf('                          rho*=%0.3f kg/m^3\n',rho_c);
+V_c=sqrt(k*R*T_c*1000);// m/s
+printf('                          V*=c*=%0.1f m/s\n',V_c);
+
+//(b)For Ma_2=2,by using data from Table A–13
+P_e=0.1278*P_0;// MPa
+printf('(b)The exit plane conditions,P_e=%0.4f MPa\n',P_e);
+T_e=0.5556*T_0;// K
+printf('                             T_e=%0.1f K\n',T_e);
+rho_e=0.23000*rho_0;// kg/m^3
+printf('                             rho_e=%0.3f kg/m^3\n',rho_e);
+A_e=1.6875*a;// cm^2
+printf('                             A_e=%0.2f cm^2\n',A_e);
+Ma_e=1.6330;// Critical Mach number
+V_e=Ma_e*V_c;// m/s
+printf('                             V_e=%0.1f m/s\n',V_e);
+c_e=sqrt(k*R*T_e*1000);// The speed of sound at the exit condition in m/s
+V_e=Ma_2*c_e;// m/s
+
+//(c)
+m=rho_c*(a*10^-4)*V_c;
+printf('(c)The mass flow rate,m=%0.2f kg/s\n',m);