本文關(guān)鍵詞： 乘波體 密切錐 黏性 后掠角 渦升力　出處：《航空學(xué)報》2016年10期 　論文類型：期刊論文

【摘要】：對定后掠角密切錐乘波體(OCWRCAS)的生成方法和考慮黏性的設(shè)計方法進行了研究。定后掠角乘波體的前緣具有特定的后掠角,能夠在上表面產(chǎn)生穩(wěn)定分離渦從而改善乘波體的氣動性能。本文首先在傳統(tǒng)密切錐乘波體生成方法的基礎(chǔ)上給出了定后掠角密切錐乘波體的生成方法;從前緣后掠的幾何特征中提取了后掠角、激波角和前緣曲線程度等設(shè)計變量,并研究了設(shè)計變量的取值范圍;以遍歷設(shè)計空間的思路對兩類定后掠角密切錐乘波體進行了設(shè)計分析,研究了升阻比、體積效率隨設(shè)計變量的變化規(guī)律,然后在設(shè)計空間內(nèi)進行了多目標(biāo)尋優(yōu);最后使用計算流體力學(xué)方法對定后掠角乘波體的乘波特性和渦升力特性進行了驗證。結(jié)果表明,由本文生成方法得到的定后掠角密切錐乘波體具有明顯的乘波特性并且能夠在較高的升阻比時保證一定的體積效率;定后掠角前緣能夠在一定的迎角下在上表面產(chǎn)生穩(wěn)定的分離渦,產(chǎn)生渦升力。
[Abstract]:In this paper, the generation method and the design method considering the viscosity of OCWRCAS are studied. The leading edge of the constant sweep angle multiplicative body has a special backward sweep angle. The steady separation vortex can be generated on the upper surface to improve the aerodynamic performance of the wave-multiplicative body. Firstly, based on the traditional generation method of the closely conical wave-multiplicative body, the generation method of the cone-multiplicative body with fixed back angle is presented. The design variables such as sweep angle, shock angle and the degree of leading edge curve are extracted from the geometric features of the leading edge swept back, and the range of the design variables is studied. Based on the idea of ergodic design space, the design analysis of two kinds of conical wave bodies with fixed back angle is carried out, and the variation law of lift / drag ratio and volume efficiency with design variables is studied, and then the multi-objective optimization is carried out in the design space. Finally, the computational fluid dynamics method is used to verify the multiplicative wave characteristics and vortex-lift characteristics of the constant sweep wave body. The results show that, The close cone multiplicative wave with constant sweep angle obtained by the method obtained in this paper has obvious multiplicative wave characteristics and can guarantee certain volume efficiency at higher lift-to-drag ratio. At a certain angle of attack, the leading edge of the fixed sweep angle can produce a stable separation vortex on the upper surface, resulting in vortex lift.
【作者單位】： 中國空氣動力研究與發(fā)展中心計算空氣動力研究所;
【分類號】：V211.41

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