| 机翼边界层计算及其在飞机设计中的应用 |
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| 引用本文： | 包涵龄.机翼边界层计算及其在飞机设计中的应用[J].航空学报,1987,8(11):553-560. |
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| 作者姓名： | 包涵龄 |
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| 作者单位： | 中国气动研究与发展中心 |
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| 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。
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| 收稿时间： | 1986-06-17; |
WING BOUNDARY LAYER CALCULATION AND IT'S APPLICATION TO THE AIRCRAFT DESIGN |
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| Bao Hanling.WING BOUNDARY LAYER CALCULATION AND IT'S APPLICATION TO THE AIRCRAFT DESIGN[J].Acta Aeronautica et Astronautica Sinica,1987,8(11):553-560. |
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| Authors: | Bao Hanling |
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| Institution: | China Aerodynamic Research and Development Center |
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| 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. |
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