绕AOTV高超音速流场的数值计算

NUMERICAL COMPUTATION OF HYPERSONIC FLOWS OVER AOTV CONFIGURATION

本文采用实质上为二阶精度的隐式无波动、无自由参数耗散(NND)差分格式结合Steger-Warming矢通量分裂方法求解N-S方程,对AOTV外型的高超音速绕流进行了模拟。在计算中,对脱体激波采用了捕获法。作为验证,首先计算了二维圆柱绕流,并同文献[1]的数据进行了比较,取得了满意的结果,算例的计算结果还表明,采用本文的方法对激波的模拟具有较高的分辨能力。

An essentially second order accuracy procedure for solving N-S equations is constructed based on an implicit, non-oscillating, no-free-parameter, and diffusive (NND) finite difference scheme, in conjunction with Steger-Warming flux vector splitting technique. The developed scheme with shock capturing approach is employed to compute the complex flow fields over AOTV-like configuration. A flowfield over a semi-cylindrical body computed by the present procedure is presented first in this paper and compared with the data given in Ref[1]. revealing in good agreement. The numerical results given in the test case demonstrate that the present scheme can provide a high resolution on simulating hypersonic flows with shocks.