关键词: 势流, 有限差分理论, 机身－机翼构型, 可压缩流

Abstract: The “H-O” grid is suggested in this paper to compute the compressible flow past highly swept slender wing-body combinations. Full-potential equation,finite difference method and approximate factorization iteration scheme are used. The computation for the AGARD-B wing-body shows that the code developed can be applied to the cases from subsonic up to low supersonic free streams. The computed lift and moment are in good agreement with the experimental results.

Key words: potential, flow finite-difference, throey body-wing, configurations, compressible flow