弹用高亚音速S形进气道设计和试验研究

A STUDY ON HIGH SUBSONIC S-SHAPED INLETS IN MISSILES

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

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

摘要:

简要介绍弹用涡轮喷气发动机的一系列高亚音速Ｓ形进气道气动设计和试验研究结果，并提出了关于高亚音速Ｓ形进气道在弹上的位置、进气道长度、进口形状、进口面积、内外唇口以及Ｓ形通道型面等设计的基本准则。通过风洞模型试验和发动机／进气道匹配试验，发现不同弹体布局对进气道性能的影响。借助激光技术观察并记录了弹体涡在一定攻角情况下进入Ｓ形腹部进气道的现象，与其它测试结果相配合，证实了弹体涡、弹翼波以及附面层的互相干扰对进气道性能影响的严重性。

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.