关键词: 超音速冲压喷气发动机;高超声速进气道;Busemann进气道+;进气道设计

Abstract: A partial Busemann inlet was designed for Mach 5.3 flight and has a contraction ratio of 8 and was tested in the wind tunnel at Mach 5.3,which is applied to the inward turning air-breather.Distributions of the static pressure along the centerlines of the top wall,sidewall and cowl bottom wall,and Pitot-pressure of the isolator exit plane were experimentally obtained.Static pressure distributions were compared with the numerical results simulated by Fluent software and show good agreement.The characteristics of inlet on compression and waveride were analyzed.Experimental results indicate the inlet has a better performance with a mass capture ratio 0.58,averaged Mach number 1.4,total pressure recovery 0.217,and compression pressure ratio 37.6 at the isolator exit plane.

Key words: Supersonic combustion ramjet engine;Hypersonic inlet;Busemann inlet~+;Inlet design