关键词: 进气道一发动机匹配;进气道－机身构型;风洞试验;匹配试验;气动设计;设计要求

Abstract: n this paper the results of aerodynamic design and experimental re-search of a series of high subsonic S-shaped inlets used for turbojet engines of winged missiles are simply introduced. According to the characteristic of mlssilebourn inlets and the research results, basic design principles to locate the inlet in missile, length of inlet, entrance shape, entrance area, the inner and outer lips and the sections of S-shaped passage are proposed.During the model experiments in wind tunnel and engine/inlet match experiments, the influences of different fuselarge arrangement properties of inlets. With the help of laser technics, the phenomina that the fuselarge vortex enters into the vertral S-shaped inlet under certain attack angle are observed and recorded. Associated with other testing results, the significance of influence of the disturbances among the fuselarge vortex, wing shock and the boundary layer on the properties of inlets is proved.

Key words: Inlet-engine matching;Inlet-airframe configuration;Wind tunnel test. Matching test. Aerodynamic design;design requirement