弹体级间分离流场特性的数值模拟研究

THE NUMERICAL STUDY OF FLOWFIELDS AROUND A SEPARATING MISSILE

用数值方法模拟了超声速弹体级间分离流场 ,给出了不同级间距离时几种典型的流场结构 ,两类典型的流态与实验观察一致。级间距离较小时 ,级间区为死水区 ,前体阻力为负 ,出现典型的“后体效应”现象 ;距离较大时 ,内外流之间出现很复杂的干扰波系 ,一定的分离距离后 ,后体前缘分离流动区前出现正激波 ,后体的干扰基本被隔绝。

The flowfields around a separating missile in supersonic free stream are studied numerically. Several typical flowfield structures in various separation distances are obtained. Two typical flow patterns are consistent very well with that observed in experiment. When the separation distance is small, the region between two stages is filled with “dead water” flow, the bottom drag of forebody is negative, the typical “afterbody effect” phenomenon occurs. When the separation distance is large, the complex interactive waves system is observed. After centain separation distance, the normal shock wave is formed in the front of the separated flow region before afterbody, hence the afterbody effect to forebody has been cut off.