Space-shuttle main engine is designed with the given criteria x design altitude = 60,000 feet (18,300 m), where atmospheric pressure is, patm=7171.64 pa= 1.04016 psi. at this altitude the exhaust jet is fully expanded. x nozzle exit mach number = 5.05 (calculated) x throat area = 93 square inches (600 cm2) x nozzle exit area = 50.265 square feet (4.6698 m2 ) x chamber total pressure = 2,747 pounds per square inch (18,940 kpa) at 100% power assuming you can use the 2-d shock/expansion theory: calculate the static pressure at the nozzle exit plane and the flow-turning angle right after the flow exits the nozzle at: x sea level, where patm = 101325 pa =14.696 psi x b) 100,000 feet, where patm = 1090.16 pa = 0.158 psi