带减阻杆高超声速飞行器外形气动特性研究  

Investigations on aerodynamics of the spike-tipped hypersonic vehicles

作　　者：姜维[1,2] 杨云军[2] 陈河梧[2] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073 [2]中国航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2011年第6期28-32,53,共6页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金重大研究计划资助项目(90916001)

摘　　要：采用高超声速风洞测力试验方法测量钝头飞行器头部减阻杆的高超声速气动特性,研究减阻杆的气动减阻原理,分析了多组不同构型减阻杆的减阻效果。结果表明,减阻杆显著减少了钝头飞行器高超声速的阻力,最大的减阻率达到60%之多;减阻效果与减阻杆构型和迎角状态密切相关;减阻杆会诱发稳定性、'热斑'以及非定常脉动等不利问题。In this paper, aerodynamics of the spike-tipped vehicles has been investigated utilizing hypersonic wind tunnel experiment to analyze rules of drag reduction. The results indicate that the drag of hypersonic vehicle is reduced sharply with a spike which changes flow structure. The maximum of drag reduction is higher than 60%. Drag reduction is tightly releated to angle of attack and the configurations of spike. However, the spike-tipped vehicle will bring about some disadvantages such as weak stability, heat spot and unsteady flow fluctuation.

关 键 词：高超声速流 风洞实验 钝头飞行器 减阻杆 弓形激波 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]