关键词: 操纵面;二维流;流场;计算

Abstract: Two-dimensional flow field around the cross Section of gas rudder in gas flow direction is calculated. In calculation, the flow field is divided into three regions: subsonic-transonic region Ⅰ behind curved shock wave around blunt-nosed body, supersonic region Ⅱ behind curved shock wave and supersonic flow region Ⅲ behind expansion wane. The Strip-band method, characteristic method and Prandtl-Meyer formula are used, respectively, to calculate flow parameters in terms of the consideration of aerodynamics, thermodynamics, ablation, heat transfer and stress.

Key words: Control surface;Two-dimensional flow;Flow field;calculation