超音速绕凹角湍流分离流动的计算

本文用统一的Levy-Lees变换以及正算法与逆算法相结合,求解了超音速绕凹角湍流分离流动。 对附着流区用边界层正算法,压强分布用流过尖劈统一的高超音速与超音速公式,湍流模型取代数涡粘性模型;对凹角分离区用边界层逆算法,给定位移厚度δ~*分布,湍流模型取代数松弛模型;边界层计算采用Cebeci-Keller Box方法;计算成功地算得分离流场,较好地预估了分离点与重附点位置以及壁面压强分布与表面摩擦应力分布。

COMPUTATION FOR SUPERSONIC AND TURBULENT SEPARATED FLOW OVER A COMPRESSION CORNER

By using unified levy-lees tranformation and direct/inverse method, a numerical solution for supersonic and turbulent separated flow over a compression corner is presented.A direct method is applied with given pressure distributions which is obtained by the unified supersonic/hypersonic small, disturbance theory over a wedge. The turbulent model adopted is the simple algebraic "eddy viscosity" model.An inverse method is used for the separated flow region in which the displacement-thickness d* is prescribed with pressure treated as unknown parameter. Turbulent model adopted is the algebraic relaxation model.The Keller Box Scheme is used to solve the boundary layer equations.The computation predicts separated point, reattachment point, the wall pressure and the skin friction stress distribution well.