| 跨音速机翼设计方法的改进 |
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| 引用本文： | 孙若姿,华俊.跨音速机翼设计方法的改进[J].北京航空航天大学学报,2003,29(3):269-272. |
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| 作者姓名： | 孙若姿 华俊 |
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| 作者单位： | 北京航空航天大学 飞行器设计与应用力学系 |
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| 摘 要： | 以Takanashi提出的"正反迭代、余量修正"的原理为基础,针对其当机翼上表面存在较强的超音速流动时,解的收敛性不好的问题,对Takanashi方法进行改进.具体方法就是在控制方程的双曲部分引入基于迎风格式的附加项.通过对某干线飞机机翼的设计,证明了改进后的方法是成功的,设计结果在超音区有很好的收敛性.
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| 关 键 词： | 机翼 超音速流动 激波 迎风格式 |
| 文章编号： | 1001-5965(2003)03-0269-04 |
| 收稿时间： | 2001-10-22 |
| 修稿时间： | 2001年10月22日 |
Modification of Transonic Wing Design Method |
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| Sun Ruozi,Hua Jun.Modification of Transonic Wing Design Method[J].Journal of Beijing University of Aeronautics and Astronautics,2003,29(3):269-272. |
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| Authors: | Sun Ruozi Hua Jun |
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| Institution: | Dept. of Flight Vehicle Design and Applied Mechanics, Beijing University of Aeronautics and Astronautics |
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| Abstract: | The residual correction design method for transonic wings with prescribed pressure distribution developed by Takanashi was modified. In order to guarantee the convergence of the design in supersonic flow, Takanashi method could be modified by introducing some upwind based operator to the governing equation in hyperbolic parts. Results of the redesign of a wing indicate that the improved method can overcome the convergence problem of the original method in supersonic region and then is more practical in engineering application. |
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| Keywords: | wings supersonic flow shock waves up wind discrezation |
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