摘要
针对高超声速流动中的高温真实气体效应,采用数值模拟求解三维N-S方程的方法研究了壁面催化对高超声速飞行器气动特性的影响规律。研究发现:对于文中所选两类高超声速飞行器———大钝头CEV再入飞行器和仿HTV2高升阻比升力体飞行器,壁面催化对表面压力影响均较小,对剪切应力的影响在飞行器不同部位表现不同:在头部和前缘等强压缩区域,壁面催化对表面剪切力影响明显,在大面积和背风区位置,壁面催化对表面剪切力影响微弱。这是因为壁面催化使得具有更大惯性的大分子气体在近壁处聚集,从而导致更高的速度梯度。由于大钝头外形波阻在整体气动特性中占优,而高升阻比外形头部强压缩区域面积较小,头部强压缩区域剪切力对整体气动特性贡献较小,最终体现为壁面催化对整体气动力影响微弱。
For the research on high temperature real gas effects of hypersonic flows,numerical simulation is applied to study surface recombination effect on aerodynamic characteristics by solving the 3-D NavierStokes equations.The studied vehicles include two types,one is the CEV-alike configuration,and an other is the HTV2-alike configuration with high L/D.The results show that surface catalytic Had less influence on the wall pressure.The wave drag is almost the same at different catalytic conditions,while the surface friction differs from each other obviously around the high compressed area,but the difference is small in the major area and backward area.Surface recombination makes big molecule congregate to the wall,which causes larger velocity gradient.Wave drag is dominated to blunt body re-entry because there is a characteristic of base compressed flow.But to the high L/Dflight,because the high compressed area is small,which contributes to the whole loads unapparent,and finally the whole drag coefficient varies with the surface recombination conditions very slightly.
出处
《空气动力学学报》
CSCD
北大核心
2014年第2期235-239,共5页
Acta Aerodynamica Sinica
关键词
高超声速
壁面催化
气动特性
剪切力
N-S方程
hypersonic
surface recombination
aerodynamic force
surface friction
Navier-Stokes equation
