摘要
针对传统的与钝体轴线共线安装的固定式激波针方法在有攻角状态所存在的问题,在前人工作基础上得到一种新型高超声速飞行器减阻/降热方法——自适应激波针方法.将该方法应用于三维高超声速轴对称钝锥外形以及扁平楔外形,并采用数值模拟的方法对其进行了概念验证.在0°～12°攻角范围内,对不同L/D参数的激波针外形流场以及前缘壁面的压力、热流分布等进行了对比分析.结果表明,这种新型自适应激波针方法在攻角从0°～12°,均可有效降低高超声速飞行器头部壁面的压力和热流,有效解决了传统激波针方法在较大攻角状态下失效的问题.
The conventional fixed spike method,in which the spike is mounted with an alignment along the body-axis,always failed at relatively high angles of attack;therefore,a new self-aligning spike method is investigated in the present paper.This method is applied to 3D axi-symmetrical blunt cone and compressed wedge configurations at hypersonic speeds.Numerical simulations are carried out to verify this new concept. Spiked geometries with different L/D parameters at angle of attack ranged from 0 to 12 degrees are investigated. Numerical results reveal that the self-aligning spike method has great capability in drag and heat reduction as compared with the conventional fixed spikes.It can still effectively work even at relatively large angles of attack.This new method can resolve the problem that encountered by the conventional spike method.
出处
《力学学报》
EI
CSCD
北大核心
2011年第3期441-446,共6页
Chinese Journal of Theoretical and Applied Mechanics
基金
国家自然科学基金资助项目(90716010)~~
关键词
高超声速
减阻
热流
激波针
数值模拟
hypersonic
drag reduction
heat flux
aerospike
numerical simulation
