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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。
In this paper, a method for solving the two-dimensional compressible turbulent separation boundary layer integral method is introduced. In the method, the boundary layer momentum integral equation and the average flow energy integral equation are taken as the basic equations. The Swafford velocity-type analytic equations for the attachment and detachment of turbulence are used to calculate the dissipation of four algebraic vortex viscosity models Integral and the influence of boundary layer parameters. The calculated results are in good agreement with the measured data of the transonic airfoil boundary layer with strong interference of the shock boundary layer. This method can be extended to calculate the wake characteristics of airfoils.