关键词: 亚音速进气道;跨音速进气道

Abstract: The present paper briefly reviews the domestic research work,during past ten years, on subsonic and transonic S-shaped inlet used in missiles and summarizes some progress in recent years in inlet design,numerical methods for the calculation of flow fields inside and outside inlet, inlet/engine compatibility, measuring and testing technology, and data processing etc. Up to now, the basic design criterions, the methods to determine the inlet/engine compatibility conditions in test and the simulation of coming air flow conditions have been proposed,and numerical methods have been used in choice of the shapes of the lips and the turning passage,and the methods for measuring the outlet pressure pattern under stable conditions and the corresponding data processing have also been studied. The total pressure recovery σ=0.98-0.99,total pressure distortion DC60 = -0.20--0.30 and total pressure nonuniformity D= 5% are obtained at highsubsonic speed with fineness ratios of 3.5-5 and axis defection angles of 35°-38.5°.

Key words: Subsonic inlet;Transonic inlet