Numerical computation of hypersonic flows over AOTV configuration

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 flow field 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 a 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.