d. If the first stage reaches Mach 10 at 75 km, calculate the fuel mass fraction. assume n0=0.5, hPR=120,000 kJ/kg, (1-D/FN)=0, T=208K, vi=0 m/s.

In previous steps, mass flow rate was found to be 544.71 kg/s, chamber pressure is 100 atm, and chamber temperature is 4000 K. Nozzle exit area is 1.04 m^2, and the fuel has: R= 375 J/kgK, gamma=1.26

This is a propulsion question