可压缩紊流分离边界层的计算

 本文介绍了一种求解二维可压缩紊流分离边界层的正反积分方法。该方法以边界层动量积分方程和平均流动能积分方程作为基本方程,采用适用于贴附和分离紊流的Swafford速度型解析式,对比计算了四种代数涡流粘性模型对沿流向各点的耗散积分及诸边界层特征参数的影响。计算结果和存在激波边界层较强干扰的跨音速翼型边界层的测量数据吻合。该方法可扩展用于计算翼型的尾迹特性。

CALCULATION OF COMPRESSIBLE TURBULENT BOUNDARY LAYERS WITH SEPARATION

An integral method associated with direct and inverse mode is presented for the calculation of compressible turbulent boundary layer with separations over airfoil. The method employs the momentum integral equation and a mean-flow kinetic energy equation, and makes use of Swafford' s velocity profile expression. Four different algebraic eddy viscosity models are used to evaluate the dissipation integral at each streamwise location. The effect on the boundary layer development is analysed. Comparisons are made with experimental data on the interaction between shocks and turbulent boundary layers over the transonic airfoil. Finally, the method is extended to handling airfoil wakes.