高超声速飞行器体襟翼局部分离流动数值研究  

Numerical study on local separation flow over body flaps of hypersonic vehicle

作　　者：石磊[1] 龚安龙[1] 杨云军[1] 周伟江[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2017年第4期510-515,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(11372040)

摘　　要：采用全Navier-Stokes方程的计算流体力学模拟技术研究了类HTV-2高超声速飞行器体襟翼局部分离流动特性,分析了不同飞行高度、壁面温度、飞行迎角等对流动分离特性的影响。研究表明:随着高度增加,壁面附近压力分布发生改变,沿着流向所形成的逆压梯度不断减小,使得体襟翼与飞行器表面附近的分离区减小;壁面温度增加导致压缩拐角(体襟翼与飞行器表面间)上游的流向速度梯度减小,即壁面粘性力减小,从而使分离区增大;随着迎角增加,压缩拐角内的逆压梯度增大,但上游流向速度梯度增加带来的黏性力增大更为明显,使流动更不容易发生分离,即分离区减小。The computational fluid dynamics（CFD） simulation technique based on Navier- Stokes equations is used to study the local separation flow characteristics of the flaps of the HTV- 2 hypersonic vehicle. The effects of different flight altitude, wall temperature and flight angle on the separation characteristics are analyzed. As the altitude increases, the adverse pressure gradient formed along the flow direction decrease, resulting in a smaller separation zone near the flaps and the surface of the aircraft. Increasing wall temperature leads to the streamwise velocity gradient upstream of the compression corner decreases, thereby increasing the separation zone. With the angle of attack increases, adverse pressure gradient increases. However, the viscous force increasing is more obvious, the flow separation is less likely to occur and the separation zone is reduced.

关 键 词：计算流体力学 高超声速流动 体襟翼 逆压梯度 流动分离 

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]