- 1 25 Pts Mo 2 3 14 A1 10 A2 A 2d External Compression Supersonic Inlet Designed For A Flight Mach Number Of 2 3 H 1 (152.68 KiB) Viewed 16 times
1. (25 pts) Mo = 2.3 14° A1 10° A2 A 2D external-compression supersonic inlet designed for a flight Mach number of 2.3 has a first compression ramp at 10 deg and a second ramp at 14 deg additional deflection. Thus the inlet shock system has two external oblique shocks with a normal shock at the inlet throat. There is a subsonic diffusion section downstream of the normal shock with area ratio A2/A1 = 1.22 For this inlet at its design condition determine the following: a) Inlet total pressure recovery Pt2/Pto based on shock losses b) Mach number at the engine face M2 Assume isentropic flow in the subsonic diffuser section with y = 1.4