摘要
显式、二阶精度、总变差下降（TVD）有限体积格式解无粘、可压缩气体流动方程组。数值仿真了跨、超音速气体沿圆锥绕流的前部流场。获得波后流场的等压力线、等密度线、等马赫线和圆锥表面的压力系数，确定了锥激波的几何位置。仿真结果与精确解和实验结果吻合较好。
An explicit,second-order accurate,total variation diminishing (TVD) scheme in finite volume form is employed to solve inviscid,compressible aerodynamics equations.The gas transonic,supersonic now around a cone's forehead is simulated numerically.Pressure contours,density contours,Mach number contours and pressure coefficient on the cone are obtained.Conical shock wave position is geometrically determined.The results of simulation are shown to be in close agreement with experimental data and the accurate solutions.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
1996年第4期362-365,共4页
Acta Armamentarii
