The scramjet engine in the first Image is supersonic throughout. The second Image shows Its sketch. Test the following
design. The flow enters at Ma = 7 and air properties for 10,000 m altitude. Inlet area is 1 m², the minimum area is 0.1 m²,
and the exit area is 0.8 m².
Ma > 1
Combustion
Ma > 1
Determine the exit Mach number, the exit velocity, and the exit pressure.
The Mach number at the exit is
The exit velocity is m/s.
The exit pressure is Pa