摘要
从包含多种组分的N S方程出发,考虑两方程湍流模型,采用NND2M差分格式,对带有横向喷流的双锥旋称体高超声速绕流场进行数值模拟,计算结果与已有的试验数据进行对比,符合较好。在此基础上对带有横向喷流控制系统、型尾翼布局、高超声速飞行的导弹外流场进行数值模拟,研究了迎角、多个喷口、热喷流效应和湍流模型对气动力特性的影响;计算表明在无尾翼情况下有/喷流的气动力差别较小,喷流影响随迎角变化不敏感;对带有尾翼的气动布局,喷口位于背风区时喷流影响较小,喷口位于迎风面时气动力变化较大,压心明显前移;多喷口产生的附加推力和力矩不等于每个单喷口线性相加;湍流模型和热喷流效应引起流场结构改变,但是对总的气动力影响不大。
A detailed numerical simulation of a lateral jet interacting with a hypersonic cross flow was performed using 3-D TLA N-S equations computational technique with the turbulent model and multiple gases model. The scheme NND2M, which is TVD type, was used. The missile configurations without and with wings were studied. The numerical simulation results for the configuration without wing were compared with experimental data which were completed in the supersonic wind tunnel of CARDC in the cases with cold jet gas. Then comparison by turbulent model and multiple gases model were made, it was that the aerodynamic coefficients for the configuration without wings were influenced much more by the angle of attack than multiple gases and turbulent model. The result shows that the influence of jet is bigger for a body with wings than that without wing, and the pressure center moved forward much more when the jet is on windward than that on leeward. The interaction for the missile with multiple jets is much complex, the aerodynamic coefficients is no-linear with the number of jets.
出处
《空气动力学学报》
EI
CSCD
北大核心
2004年第3期309-312,共4页
Acta Aerodynamica Sinica
