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针对超音速飞行器在飞行过程中要承受的强激波带来的不利波阻,本文与传统单翼进行对比,分析了Busemann超音速双翼构型的减阻原理并充分利用了双翼间激波膨胀波的有利干涉和机翼厚度减小所带来的激波减弱效应。以常规气动布局的超音速导弹为研究对象,数值计算结果表明:设计巡航条件下,来流马赫数为2.5时,采用新型双翼气动布局能够使波阻减小42%。同时,为了消除非设计马赫数下Busemann双翼构型的壅塞问题,本文探索了一种转折变形翼面技术,计算结果表明:通过控制机翼前缘入口处和最大厚度处的面积比,该方案在非设计条件下能够基本消除阻力剧增问题。此外,在Busemann双翼基础上改进的上下翼非对称的超音速双翼构型可进一步改善实际有升力飞行条件下模型的气动性能,将所计算导弹模型巡航状态的升阻比提高了22%。综合以上结果表明,本文介绍的减阻技术可以为超声速导弹的研制和发展提供新的设计思路。
Aiming at the adverse wave resistance caused by strong shocks that the supersonic aircraft must bear during flight, this paper compares the traditional single wing with the drag reducing principle of Busemann supersonic double wing configuration and makes full use of shock expansion between wings The favorable interference of the waves and the reduction of shock caused by the shock wave. The aerodynamic missile with conventional pneumatic layout is taken as the research object. The numerical results show that when the Mach number is 2.5, the new biplane aerodynamic layout can reduce wave resistance by 42% under cruise design. At the same time, in order to eliminate the congestion problem of Busemann double-wing configuration under non-design Mach number, this paper explores a turning deformation airfoil technology. The calculation results show that by controlling the area ratio of wing leading edge entrance and maximum thickness, In the non-design conditions can basically eliminate the problem of resistance surge. In addition, the improved supersymmetric supersonic wing configuration based on the Busemann wing can further improve the aerodynamic performance of the model under real lift conditions and increase the drag / drag ratio of the calculated missile model cruise state by 22%. The above results show that the drag reduction technology introduced in this paper can provide new design ideas for the development and development of supersonic missiles.