二维非均匀超音来流下最有利压缩面型面的随机选取法数值研究  

A STUDY ON OPTIMUM COMPRESSION SURFACE UNDER NON-UNIFORM 2-D SUPERSONIC FLOW CONDITION USING R. C.METHOD

作　　者：张堃元[1] 

机构地区：[1]南京航空航天大学动力工程系

出　　处：《推进技术》1994年第5期9-15,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金

摘　　要：采用近年发展起来的随机选取法，研究非均匀二维超音来流流过６种不同形状的模型压缩面时的波后非均匀超音流场。结果表明来流的非均匀性对下游流场具有重大影响。对６种不同形状楔型压缩面流场的计算表明，单纯用改变压缩面型面的办法难以减少来流的非均匀性，但是可以部分改善下游流场的非均匀程度。在研究的６种型面中，凹圆弧压缩面及等摘压缩面在本文限定的非均匀来流下，其性能优于其它４种型面的压缩面。A newly developed Random-(choice Method is used to study a two dimensional non-uniform supersonic flow field create when incoming flows passthrough six shock generators with different wedges. The numerical results strongly show the influence of incoming flow non-unifomity on downstream flow field. The computations for compression surfaces reveal that there is nearly no possible to crease incoming flow distorting, or say non-uniformity, but possible to expand it by simply changing the geometry of compression surfaces slightly of the studied six shock generators, these with concave circle configuration and isotropic configuration have better properties in non-uniformity streamwise propagation.

关 键 词：非均匀流动 超音速流动 进气道 航空发动机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]