定后掠角密切锥乘波体的生成和设计方法

Generation and design methods of osculating cone waverider with constant angle of sweepback

对定后掠角密切锥乘波体(OCWRCAS)的生成方法和考虑黏性的设计方法进行了研究。定后掠角乘波体的前缘具有特定的后掠角,能够在上表面产生稳定分离涡从而改善乘波体的气动性能。本文首先在传统密切锥乘波体生成方法的基础上给出了定后掠角密切锥乘波体的生成方法;从前缘后掠的几何特征中提取了后掠角、激波角和前缘曲线程度等设计变量,并研究了设计变量的取值范围;以遍历设计空间的思路对两类定后掠角密切锥乘波体进行了设计分析,研究了升阻比、体积效率随设计变量的变化规律,然后在设计空间内进行了多目标寻优;最后使用计算流体力学方法对定后掠角乘波体的乘波特性和涡升力特性进行了验证。结果表明,由本文生成方法得到的定后掠角密切锥乘波体具有明显的乘波特性并且能够在较高的升阻比时保证一定的体积效率;定后掠角前缘能够在一定的迎角下在上表面产生稳定的分离涡,产生涡升力。

In this paper,the generation and design methods of osculating cone waverider with constant angle of sweepback（OCWRCAS）are studied,and viscous is considered during design.Stable vortex can be generated by the leading edge with constant angle of sweepback,which will improve the aerodynamic ability of the waverider.Firstly,the generation method of OCWRCAS is presented based on the generation method of traditional osculating cone waverider.The design variables of sweepback angle,shock angle and the curve shape of head are extracted by analyzing the geometry character of the OCWRCAS,and the variation trend of lift to drag ratio and volumetric efficiency with these variables is also studied.The multiobjective optimal solutions are founded from two classical types of OCWRCAS by searching the total design space.Finally,the method of computational fluid dynamics is used to verify the character of wave riding and vortex lift.The results show that OCWRCAS with good ability of wave riding and high lift to drag ratio keeps relational volumetric efficiency;vortex lift can be generated by the leading edge with constant angle of sweepback at certain angle of attack.