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一种组合前缘乘波体设计方法及组合前缘乘波体
崔凯; 李广利; 肖尧
2017-01-04
Rights Holder中国科学院力学研究所
Abstract本发明实施例提供一种组合前缘乘波体设计方法及组合前缘乘波体,所述方法提出将乘波体外形分为机体/机翼两个部分,并进而分别采用前/后缘曲线定义的方法。从而有效改善乘波体的设计灵活性,并可获得更加贴近实际的外形。本发明实施例机翼下表面与激波面相交后形成翼前缘线,进而获得乘波体的组合前缘线采用该方法设计时,不但可以保证乘波体的特点,同时还具有长宽比例灵活可调及保证尾缘平直的优点,更加适用于实际飞行器的设计。机体下表面可采用给定前缘线的正流线追踪方法设计,机翼下表面可采用给定尾缘线的逆流线追踪方法设计。本发明主要应用范围为各类高超声速飞行器的构型设计,尤其适用于未来高超声速飞机或者滑翔类飞行器的设计
Application Date2015-02-13
Date Available2017-01-04
Patent NumberZL201510079522.X
Language中文
Country中国
Document Type专利
Identifierhttp://dspace.imech.ac.cn/handle/311007/59873
Collection高温气体动力学国家重点实验室
Recommended Citation
GB/T 7714
崔凯,李广利,肖尧. 一种组合前缘乘波体设计方法及组合前缘乘波体. ZL201510079522.X[P]. 2017-01-04.
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