The ratio AR between the area at the end of a rocket nozzle and the area of the

Question

The ratio AR between the area at the end of a rocket nozzle and the area of the nozzle's throat determines the mach number M_e of the expelled exhaust gas, and hence the thrust of the rocket. Specifically, the relationship is: AR = 1/M_e [(2/gamma + 1) (1 + M^2_e (gamma - 1)/2)]^gamma + 1/2(gamma + 1) where gamma > 1 is the specific heat ratio of the exhaust gases. Write a C++ program which will read from the keyboard a specified exit Mach number M_e and a specified gas constant gamma, then write to the screen the corresponding required nozzle aspect ratio AR computed from the formula above. For reference, when gamma = 1.4 and M_e = 2, AR = 1.687.

Explanation / Answer

#include <iostream>
#include<math.h>

using namespace std;
int main()
{
double MacNum;
double gamma;
cout<<" Enter Mac number:";
cin>>MacNum;
cout<<" Enter gamma:";
cin>>gamma;
double power=(gamma+1)/(2*(gamma-1));
double AR;
AR=(pow(((2/(gamma+1))*(1+(MacNum*MacNum*(gamma-1))/2)),power))/MacNum;
cout<<" AR= "<<AR;

}

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