Question: A rocket nozzle is designed to operate supersonically with a chamber pressure of 500 psia and an ambient pressure of 14.7 psia. Find the ratio between the thrust at sea level to the thrust in space (0 psia). Assume a constant chamber pressure, with a chamber temperature of 2500°R. Assume the rocket exhaust gases behave as a perfect gas with γ = 1.4 and R = 20 ft-lbf/lbm R.