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+clc;clear;
+//Example 17.15
+
+//given data
+P1=480;
+T1=550;
+V1=80;
+d1=15/100;//diameter in m
+AF=40;//air to fuel ratio
+HV=40000;//heating value in kJ/kg
+
+//from Table A-2a
+R=0.287;//in kJ/kg-K
+cp=1.005;//in kJ/kg-K
+k=1.4;
+
+//calculations
+p1=P1/(R*T1);
+A1=%pi*d1^2/4;
+mair=p1*A1*V1;
+mfuel=mair/AF;
+Q=mfuel*HV;
+q=Q/mair;
+T01=T1+V1^2/(2*cp);
+c1=sqrt(k*R*T1*1000);//factor of 1000 to convert kJ to J
+Ma1=V1/c1;
+//exit stagnation energy equation q= Cp (T02 - T01)
+T02=T01+q/cp;
+//from Table A–34
+//at Ma1
+//s stands for * symbol
+T0s=0.1291;//T0/Ts
+Ts0=T01/T0s;
+T2s=T02/Ts0;//T02/T*0
+//from Table A–34 at this ratio
+Ma2=0.3142;
+//Rayleigh flow relations corresponding to the inlet and exit Mach no
+//at Ma1
+T1s=0.1541;//T1/Ts
+P1s=2.3065;//P1/Ps
+V1s=0.0668;//V1/Vs
+//at Ma2
+T2s=0.4389;//T2/Ts
+P2s=2.1086;//P2/Ps
+V2s=0.2082;//V2/Vs
+T2=T2s/T1s*T1;
+T2=floor(T2);
+P2=P2s/P1s*P1;
+P2=ceil(P2);
+V2=V2s/V1s*V1;
+V2=floor(V2);    
+disp(Ma2,'Mach Number at exit');
+disp(T2,'Temperature in K');
+disp(P2,'Pressure in kPa');
+disp(V2,'Velocity in m/s')