关键词: 非均匀流;超音速流;二维流;超音速进气道;流场模拟;数值计算

Abstract: 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.

Key words: Non-uniform flow;Supersonic flow;Two dimensional flow;Supersonic inlet;Flow field simulation;Numerical calculation