高超声速滑翔飞行器气动性能的数值模拟研究  

Numerical simulation on the aerodynamic performance of hypersonic glide vehicle

作　　者：刘建霞[1] 侯中喜[1] 陈小庆[1] 高显忠[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2012年第4期22-27,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(90916016);湖南省研究生科研创新及国防科技大学优秀研究生创新资助项目(B110102)

摘　　要：由于具有高的升阻比,乘波构型被认为是高超声速滑翔飞行器的重点参考外形。考虑到高超声速条件下严重的气动加热问题,乘波构型的尖锐前缘需要进行钝化处理,其表面流动特征及气动性能也随之发生变化。基于参考弹道,本文分析了高超声速滑翔飞行器沿飞行轨迹的表面流场特征,并对其在典型飞行工况下的气动性能开展了数值模拟研究。结果表明:对于采用乘波布局设计的高超声速滑翔飞行器,其驻点流动存在三维效应,不能简单视为球头或圆柱绕流;钝化可以缓和严峻的受热形势,同时对其气动力性能造成影响:在2cm钝化半径条件下,其升阻比下降12.34%;高超声速滑翔飞行器的表面受热存在明显的分区特征,不同区域可采用不同的防热处理方法。The waverider is considered as an important candidate for the configuration of hypersonic glide vehicle （ HGV ） in terms of its high lift-to-drag ratio. Due to the severe aerodynamic heating, the sharp leading edge of waverider need be blunted, and the flow characteristics and the aerodynamic performance along the trajectory will change. In the current research, the flow characteristic of a HGV was studied based on a reference trajectory, and a numerical simulation was carried out to evaluate the performance of HGV with a blunt leading edge under a typical condition. The result indicates that the flow near the stagnation point exhibits three-dimensionality which cannot be approximated as a flow around a sphere or cylinder; the heat flux can be reduced and the aerodynamic performance of HGV may decrease as well when the leading edge is blunted ： under the condition of 2 cm radii, the lift-to-drag ratio reduces by 12.34% , and different thermal protection methods can be used in different places of HGV.

关 键 词：高超声速 乘波构型 气动力 气动热 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]