| 无激波机翼的设计方法 |
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| 引用本文： | 朱自强.无激波机翼的设计方法[J].航空学报,1988,9(11):499-508. |
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| 作者姓名： | 朱自强 |
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| 作者单位： | 北京航空航天大学 |
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| 摘 要： | 本文介绍了用虚拟气体概念进行无激波机翼设计的方法,叙述了虚拟气体方法的基本思路;给出了几种虚拟气体规律,以小扰动方程为例具体说明了在超音区内的推进计算过程。分别讨论了二维和三维情况,设计和非设计状态时的效益。最后介绍了近无激波机翼修型的工程设计方法。
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| 收稿时间： | 1987-11-07; |
A METHOD FOR SHOCK-FREE WING DESIGN |
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| Zhu Ziqiang.A METHOD FOR SHOCK-FREE WING DESIGN[J].Acta Aeronautica et Astronautica Sinica,1988,9(11):499-508. |
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| Authors: | Zhu Ziqiang |
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| Institution: | Beijing University of Aeronautics and Astronautics |
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| Abstract: | A method for shock-free wing design using "fictitious gas"concept is comprehensively introduced in the paper.The main points of this method are briefly described. Several fictitious gas laws are presented. A spece-matching procedure adopted in supersonic flow region is concretely explained.The gain in 2-D or 3-D design conditions and off-design conditions is also discussed . Finally, an engineering approach for nearly shock-free wing design is introduced. |
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| Keywords: | transonic flow airfoils wings design |
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