摘要
提出了有限体积法中的隐式ＮＮＤ格式数值求解三维全ＮＳ方程和薄层三维ＮＳ方程的方法，对绕带座舱的再入飞行器高超声速粘性流动进行数值模拟。物体的形状由钝头前体和２０°倒锥后接一个圆柱体构成。在马赫数为７和１０，攻角为１０°和２０°的自由流条件下，得出了层流流场数值结果，对飞行器前体给出了物面压力分布和加热率分布。数值结果证实了本数值方法对研究再入物体的气动加热率的精确性，以及物体周围流场详细的三维流动分离结构是适用的。
This paper presents a three-dimensional finite-volume NavierStokes solver with an implicit NND finite difference scheme. Numerical simulations are made to hypersonic viscous flow over the capsule-type reentry vehicles. Body configurations are composed of a blunt nosed forebody and 20° conical afterbody followed by a cylinder. Laminar numerical results have been obtained at the following free stream condition:free stream Mach number of 7 and 10 with the angles of attack of 10° and 20°. The surface pressure and heating distributions are presented for the flow over the forebody. The results demonstrate the accuracy of the present numerical procedure for investigating the aerodynamic heating on the forebody and the detailed structure of three-dimensional separations around the afterbody.
出处
《空气动力学学报》
CSCD
北大核心
1996年第4期475-483,共9页
Acta Aerodynamica Sinica
关键词
有限体积法
NND格式
NS方程
粘性流
finite volume method, NND scheme,Navier-Stokes equations,viscous airflows.
