摘要
从薄层近似 NS方程出发 ,采用高效 ENO差分格式 ,对超音速飞行时弹头形成的流场进行了数值模拟 ,并与已有的计算和实验数据进行比较 .弹头外形为带有倒角圆的平头 -圆柱形非常规气动布局 ,研究了倒角圆半径的影响 ,给出零攻角、马赫数M=2 .0～ 5.0范围内气动阻力的变化规律 ;
Numerical investigations on the aerodynamics of bodies with plane noses in supersonic flow were studied based on the thin layer Navier Stokes equations by using new type ENO scheme. The configurations were blunt bodies with plane noses. The drag of two configurations was presented in the region of attack angle 0 and Mach number 2.0～5.0. The heat flux with different models was investigated.
出处
《弹道学报》
CSCD
北大核心
2002年第1期45-48,共4页
Journal of Ballistics
