A chemical rocket is used for launch into earth orbit. At the end of the combusion chamber the stagnation temperature is 3000K. The molecular weight of the combustion product is 26. The gases expand isentropically as an ideal gas mixture with specific-heat ratio 1.2. The area ratio A/A* of the nozzle is 20 and the throat diameter is 0.1 m. Determine:
(a) The stagnation pressure if the expansion is correct at sea level
(b) The rocket thrust at sea level, 15-km, 30-km, and 60-km altitudes.