边缘钝化对乘波构型性能影响分析  

The Blunt Leading Edge's Influence to the Performance of Waverider

作　　者：陈小庆[1] 侯中喜[1] 刘建霞[1] 葛爱学[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2009年第4期1334-1339,共6页Journal of Astronautics

基　　金：国家自然科学基金项目(10302031)

摘　　要：基于乘波构型设计高升阻比飞行器是新型高超声速飞行器布局设计的一种有效途径。受气动热和工艺限制实际应用中需要对乘波构型具有的尖锐边缘进行钝化。为了研究钝化对乘波构型性能的影响,利用计算流体力学方法研究了不同钝化半径对乘波构型气动力和气动热的影响。分析表明:乘波构型边缘钝化可以有效降低最大热流密度,但同时也会降低布局的气动性能。随着钝化半径的增大,乘波构型的气动性能降低较为明显,但对热流密度的影响逐渐减弱。在高超声速飞行器布局设计时应综合考虑钝化对气动力和气动热的影响效应,寻找最佳的平衡点。The designing of high L/D aircraft based on waverider is an effective approach for new hypersonic aircraft aerodynamic shape design. Restricted by aerodynamic heat and processing technique, the sharp leading edge of waverider needs to be blunted. In order to study the blunt leading edge＇ s influence to the performance of waverider, the computational fluid dynamics tool is used to study different blunt radius＇ influence to waverider＇ s aero force and aero heat performance. The results show that blunt leading edge could reduce the maximum heat flux effectively, but it also reduced the aero- dynamic performance. As the blunt radius increases, the aerodynamic performance reduced significantly, but its influence to the heat flux wears off. When designing the aerodynamic shape of hypersonic aircraft, the influence of bluntness to aerodynamic force and heat flux should be considered synthetically and the best balance point should be founded.

关 键 词：乘波构型 边缘钝化 气动热 升阻比 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]