一种乘波构型边缘钝化方法的仿真与试验研究  

Numerical and experimental study of one blunt method for waverider configuration

作　　者：刘建霞[1,2] 尘军 侯中喜[2] 张扣立[1] 马晓伟[1] 

机构地区：[1]中国空气动力研究与发展中心,绵阳621000 [2]国防科技大学航天科学与工程学院,长沙410073 [3]空间物理重点实验室,北京100076

出　　处：《空气动力学学报》2014年第2期171-176,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(90916016);湖南省研究生创新项目(CX2011B002)

摘　　要：乘波构型被视为近空间高超声速飞行器的理想气动布局,但其在实施钝化修形后气动力性能损失严重,使得其实用价值受到影响。根据乘波构型的典型气动加热特征,提出了一种新的边缘钝化方法,并通过数值模拟和风洞试验相结合的研究手段对其进行了分析。结果表明:新提出的边缘钝化方法可使乘波构型在满足防热需求的同时,气动力性能得到改善;采用经过优化设计的钝化方法,钝边缘的乘波构型仍可作为近空间高超声速飞行的重要候选布局。Waverider is considered to be an ideal configuration for hypersonic vehicles in the near-space, but due to the serious aero-heating and facture limitations,its infinite sharp leading edge should be blunted which would result in a remarkable loss of aerodynamic performance and have a great effect on the practical value of waverider configuration.In this paper,one blunt method is proposed based on the typical aero-heating characteristics of waverider.Furthermore,numerical technology is used to study the flow characteristics of blunt waverider,including the mechanism of bluntness impact and the feasibility of this new blunt method.An experiment has been done in FD-14Ahypersonic shock wind tunnel to obtain the flow structure and heat flux distribution in the nose region of waverider model.The results show that bluntness induces a detached bow shock around the nose region and the phenomenon of spillage along the leading edge,which therefore results in an increment of drag and a reduction of lift and lift-to-drag ratio.However,the serious aero-heating is limited in the nose region for blunt waverider,smaller blunt radius can be used for most of the leading edge.Owing to the improvement of aerodynamic performance and negligible influence on thermal protection system,the blunt method proposed by the present paper is proved to be feasible for hypersonic waverider design.Under the studied conditions,the lift-to-drag ratio increases about 3.0%.If the blunt method is optimized,waverider configuration is still one of the most important candidates for hypersonic flight in the near-space.

关 键 词：乘波构型 钝化方法 数值模拟 风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]