跨声速翼型绕流的Euler/边界层方程干扰数值解

Numerical Solutions of Transonic Airfoil Flows by Interaction of Euler and Boundary-Layer Equations

本文利用Euler方程和可压缩湍流边界层积分方程研究绕跨声速翼型的有粘与无粘强干扰流动。应用有限差分法在贴体的网格上求解时间相关的Euler方程,以剪功积分方法求解翼面贴附和分离湍流边界层流动,并引入一个松弛方程描述剪应力对上游湍流历程的延迟响应。有粘/无粘干扰采用表面源模型。计算结果表明,对翼面存在强干扰流动情况,获得了与实验值基本吻合的结果。

Euler and compressible turbulent integral boundary-layer equations are used to analyze viscous/inviscid strong interaction flows over transonic airfoils. The time-dependent Euler equation on body-fitted meshes is solved by finite-difference scheme.By shear-work integral method, the attached and separated turbulent boundary-layer flows are computed, and a relaxation equation is applied to describe the lag process of shear stress's response to the upstream turbulent history. The viscous-inviscid interaction is achieved using the surface source model. The results in this paper are in good agreement with experiment.