Abstract
This paper proposes a new scheme called AUSMPW (AUSM by pressure-based weight functions) improved from the previous AUSM schemes by introducing the pressure-based weight functions. AUSMPW scheme is essentially developed to improve such performances as the removal of numerical oscillations near a wall and overshoot phenomena behind shock waves, which are the main shortcomings of AUSM+ scheme. In order to investigate the computational characteristics of AUSMPW in detail, it has been applied to various hypersonic flow problems. The results, compared with those of AUSM type schemes, are summarized as follows; no carbuncle phenomena and high resolution at discontinuities such as shock waves, the removal of numerical oscillations, better computational convergence, and accuracy in boundary layer. It is concluded that AUSMPW can effectively be applied to complex hypersonic flow problems.
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