弯曲进气道三维边界层预测

本文研究了弯曲进气道内三维可压缩湍流边界层的预测方法。采用非正交曲线坐标系中三维边界层积分方程,并引入掺混系数微分方程,用滞后掺混法求解,数值方法为预估-校正法,用三次样条函数解决了离散数据的插值、求导的精度问题。所编程序可在微机上运行。实例计算清楚地揭示了弯曲进气道内强横向流动对边界层发展的影响,计算所得的进气道总压恢复系数与实验值的误差为1～2％。

Prediction of 3-D Boundary Layer in the Curved Inlets

In this paper, prediction method of 3-D compressible turbulent boundary layer in curved inlets is investigated. 3-D boundary layer integral equations in nor-orthogonal currilineal coordinate system are used and solved by lag-entrainment method with introduced 3-D en-trainment coefficient equation. During numerical calculation, the prediction corrector method is employed. With cubic spline function, the interpolation and differentiation accuracy and smoothness of discreate data is ensured.The developed program may be operated on the personal computer. The influence of cross flow on boundary layer development is clearly discovered by the calculated results. The calculated pressure recovery of inlet is in good agreement with experiment data.