超声速绕凹角流动的压力分裂形式简化N－S方程数值解

Numerical Solution of Supersonic Flows over the Compression Corners Using the Pressure-Splitting Form Reduced Navier-Stokes Equations

本文从压力分裂形式的简化Ｎ－Ｓ方程出发，用Ｒｕｂｉｎ格式对超声速粘性流动进行了数值求解，给出了超声速绕凹角附着流及带有小分离气泡流动的结果，与其它数值方法所得结果相比，符合较好。

Numerical solutions of the reduced Navier-Stokers equa-tions are obtained for supersonic viscous flows.According to the eigenvalue analysis of the reduced N-S equatoins,the streamwise pressure gradient term can be split into hyperbolic and elliptic components,which are discreted by backward and forward difference respectively.A multi-sweep boundary-layer-like marching technique is used to fulfil the ellipticity of the reducedN-S equations,Results of supersonic attached and separated laminarflows over the compression corners are presented and compared with othernumerical results.The comparison shows that the numerical scheme used inthis paper is suitable to solve the problem of supersonic viscous flows withstrong adverse pressure gradient and the small separation bubbles.