旋成体超声速底压特性的并行数值研究

Parallel Numerical Investigation of the Supersonic Base Pressure Feature of an Axisymmetric Body

作用在超声速飞行器底部的压强对飞行器设计具有十分重要的意义，因为它可能提供飞行器总阻力的一半以上。目前，底压数据的来源主要还是依靠实验。而风洞实验时支杆的存在又增加了底阻估算的困难。本文用隐式有限体积法求解轴对称ＮＳ方程，在ＰＶＭ平台下数值模拟超声速底部流场，根据底压分布计算出了底压系数。分析了网格密度，支杆直径对底压系数的影响，网格足够密时，计算结果与实验吻合较好。

The pressure acting on the base of a body moving at supersonic flow may be of considerable practical importance in a vehicle design since it can provide a base drag amounting to more than one half of the total drag of the vehicle.Presently the base pressure data are dependent on experiments.The existence of a support sting causes the difficulty of the base drag estimation in wind tunnel test,too.This paper uses an implicit finite volume method to solve axisymmetric N S equations to simulate supersonic base flow fields numerically in the PVM platform. Base pressure coefficients are calculated by a base pressure distribution.The effect of the grid density and the sting diameter on results is studied.Numerical results are coincident with experimental results when the grids are sufficiently clustered.