For a booster rocket, the chamber conditions are given as Tc = 3500 K, Pc = 6 MPa, with the molecular mass and ratio of specific heat of hot gases being 22 kg/kmole and 1.22 respectively. The universal gas constant R0 is 8.314 J/mole-K. The gases are expanded through a convergent divergent nozzle designed to operate at ground conditions (0.1 MPa) with a throat area of 0.7 sq. m. The thrust generated by the nozzle is 6000 KN with a propellant flow rate of 2500 kg. Determine (i) C* efficiency (ii) Thrust correction factor.

For a booster rocket, the chamber conditions are given as Tc = 3500 K, Pc = 6 MPa, with the molecular mass and ratio of specific heat of hot gases being 22 kg/kmole and 1.22 respectively. The universal gas constant R0 is 8.314 J/mole-K. The gases are expanded through a convergent divergent nozzle designed to operate at ground conditions (0.1 MPa) with a throat area of 0.7 sq. m. The thrust generated by the nozzle is 6000 KN with a propellant flow rate of 2500 kg. Determine (i) C* efficiency (ii) Thrust correction factor.