定后掠角密切锥乘波体的生成和设计方法

发布时间：2018-02-11 11:24

本文关键词： 乘波体密切锥黏性后掠角涡升力　出处：《航空学报》2016年10期 　论文类型：期刊论文

【摘要】：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。
[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.
【作者单位】：中国空气动力研究与发展中心计算空气动力研究所;
【分类号】：V211.41

【相似文献】