【摘要】 本文给出一种计算实际机翼可压缩层流-紊流三维边界层的新方法。方法使用了Cebeci提出的一种非正交坐标系,并采用一种二次变换以克服在某处横流发生反号时计算遇到的困难。对Lockheed C-5A机翼和F-8超临界机翼给出了一系列计算结果,并同其它方法的结果以及试验数据作了比较。更多还原

【Abstract】 A new method for calculating three-dimensional compressible laminar. and turbulent boundary layers on practical wings is described in this paper. In the method, a nonorthogonal coordinate system proposed by Ce-beci is used, and a secondary coordinate transformation is suggested to overcome difficulties arised when negative transverse velocities appear locally. Several computational results for Lockheed C-5A aircraft wing and F-8 supercritical wing are given in the paper, and comparisons with other methods and with experimental data are made as far as possible.更多还原