高超声速楔形体前缘优化  

Optimization of Power Law Leading Edges in Hypersonic Flow

作　　者：赵以强[1] 刘世英[1] 邓立君 

机构地区：[1]山东理工大学交通与车辆工程学院,山东淄博255049 [2]山东滨州渤海活塞股份有限公司,山东滨州256602

出　　处：《内燃机与动力装置》2013年第2期36-39,45,共5页Internal Combustion Engine & Powerplant

摘　　要：利用N-S方程对高速飞行器的幂次前缘楔形体的高超声速绕流流场进行了分析。通过从减阻和降热的角度对楔形体前缘幂次外形的前缘钝度进行优化,确定了最优化的前缘外形,并对优化外形的逆向喷流减阻情况进行了数值模拟分析,发现逆向喷流减阻能达到48.6%;而且喷流使前缘驻点热流明显降低,有效地削弱了驻点处气动加热现象。The hypersonic flow field around a bluff body with a power law shape at the leading edge is simulated by solving N - S equation. The optimization of the leading edge bluntness is car- ried out in consideration of drag reduction of the body and minimizing the heat flux at the stagnation point at the leading edge and an optimization shape is determined. Further study on drag reduction with this optimization shape is conducted by applying a jet from the front edge opposing the hyper- sonic coming stream. It is found that the heat flux obviously decreases and the drag reduction can reach as high as 48.6%.

关 键 词：高超速流 减阻 钝体绕流 前缘优化 

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]