| 跨音速三维多升力面气动设计 |
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| 引用本文： | 杨青真,张仲寅,郑勇.跨音速三维多升力面气动设计[J].中国航空学报,2006,19(1):24-30. |
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| 作者姓名： | 杨青真 张仲寅 郑勇 |
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| 作者单位： | [1]School of Dynamics and Energy, Northwestern Polytechnical University, Xi＇an 71002, China [2]School of Aeronautics, Northwestern Polytechnical University, Xi＇an 71002, China [3]Institute of Aerodynamics and Flow Technology, German Aerospace Center （ DLR ） , Braunschweig 38108, Germany |
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| 基金项目： | China-Germany Aeronautic Technology Cooperation Project （CAE DLR Cooperation Topic 2003-03）, |
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| 摘 要： | 发展了一种跨音速多升力面的气动设计方法和设计程序,它基于已成功应用于亚、跨音速机翼设计和亚音速双翼面设计的"余量修正迭代"概念.当升力面上出现超音速区和激波时自动引用迎风格式对控制方程进行修正.开发了一系列接口程序,包括目标压力设计程序.由此气动设计程羊、TAU程序以及相应的接口程序建立了跨音速多升力面气动反设计软件系统.用两个鸭翼-机翼构型验证了设计方法和设计程序,结果表明在高跨音速下设计迭代有很好的收敛性.
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| 关 键 词： | 气动设计 跨音速流 余量修正迭代 多升力面 鸭翼 机翼 aerodynamic design transonic flow iterative residual correction multi-lifting surfaces canard wing |
| 文章编号： | 1000-9361（2006）01-0024-07 |
| 收稿时间： | 2005-05-25 |
| 修稿时间： | 2005-10-11 |
Aerodynamic Design for Three-Dimensional Multi-lifting Surfaces at Transonic Flow |
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| Thomas Streit,Georg Wichmann,YANG Qing-zhen,ZHANG Zhong-yin,Thomas Streit,Georg Wichmann,ZHENG Yong.Aerodynamic Design for Three-Dimensional Multi-lifting Surfaces at Transonic Flow[J].Chinese Journal of Aeronautics,2006,19(1):24-30. |
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| Authors: | Thomas Streit Georg Wichmann YANG Qing-zhen ZHANG Zhong-yin Thomas Streit Georg Wichmann ZHENG Yong |
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| Institution: | 1. School of Dynamics and Energy, Northwestern Polytechnical University, Xi''an 71002, China;2. School of Aeronautics, Northwestern Polytechnical University, Xi''an 71002, China;3. Institute of Aerodynamics and Flow Technology, German Aerospace Center (DLR), Braunschweig 38108, Germany |
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| Abstract: | An aerodynamic design method and corresponding codes are developed for three dimensional multi-lifting surfaces at transonic flow. It is based on the “iterative residual correction” concept that is successfully used for transonic wing design and subsonic multi-lifting surface design. The up wind scheme is introduced into governing equations of multi-lifting surface design method and automatically acted when supersonic flow appears on the surface. A series of interface codes are programmed, including a target- pressure modification tool. Using the improved inverse aerodynamic design code, T A U code and interface codes, the transonic multi-lifting aerodynamic design software system is founded. Two cases of canardwing configuration have been performed to validate the method and codes. The results show that the convergence of analysis/design iteration is very good at higher speed transonic flow. |
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| Keywords: | aerodynamic design transonic flow iterative residual correction multi-liftlng surfaces canard wing |
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