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+clear
+clc
+//Example 12.9 MASS FLOW RATE IN SUPERSONIC WIND TUNNEL
+k=1.4;
+R=287; //[J/kg.K]
+M=3; //Mach number
+A=225*10^-4; //[m^2]
+//Throat area
+Ao=A/((1/M)*{(1+[(k-1)/2]*M^2)/((k+1)/2)}^((k+1)/(2*(k-1)))) //[m^2]
+//Static T,p 
+T=273+(-20) //[K]
+p=50; //[kPa]
+//Total temperature
+Tt=T*(1+(k-1)*M^2/2) //[K]
+//Total pressure
+pt=p*(1+(k-1)*M^2/2)^(k/(k-1)) //[kPa]
+//Mass flow rate
+m=k^(1/2)*[(2/(k+1))^((k+1)/(2*(k-1)))]*pt*10^3*Ao/((R*Tt)^(1/2)) //[kg]
+printf("\n The mass flow rate = %.1f kg/s.\n",m)
+\ No newline at end of file