Consider a normal shock wave at 3 km altitude with a flow Mach number of 2.5 and a pressure ratio, P2/P1 = 3.0 . Find t
Posted: Mon May 23, 2022 10:50 am
Consider a normal shock wave at 3 km altitude with a flow Mach number of 2.5 and a pressure ratio,
P2/P1 = 3.0 . Find the pressure, density, temperature, velocity, and Mach number downstream of the wave.
P2/P1 = 3.0 . Find the pressure, density, temperature, velocity, and Mach number downstream of the wave.