Question

A supersonic diffuser with spike at inlet is design to operate at critical mode when it flying at Mach=2.8. The ambient pressure and temperature are 80kpa and 280 K respectively. If the diffuser inlet area is 0.35m2 and the diffusers exit velocity is 50 m/sec. Determine
a) The mass flow rate pass through the diffuser..
b) The total stagnation pressure loss
c) The diffuser exit area Ae, and the static pressure Pe.
M=2.8, P=50???

angle 20 degree
T∞=280
50m/sec

Answer 1