超声速场中的反向喷流数值模拟  

Numerical simulation on opposing jet in hypersonic flow

作　　者：田婷[1] 阎超[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2008年第1期9-12,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：采用了高分辨率的N-S(Navier-Stockes)方程数值模拟方法,对钝头体头部反向喷流进行研究.计算并分析了头部反向喷流现象中喷流马赫数、来流马赫数、攻角等因素对流场细致结构的影响,并对反向喷流减少阻力和减少气动加热的原理进行了深入分析和探讨.研究分析表明这些因素通过决定弓形激波、马赫盘的强度和位置,来影响回流区的大小和位置,从而使有反向喷流时阻力系数所受到的影响比无喷流时更大.The detailed influences of the free mach number, jet mach number, attack angle on the drag coefficient reduction were studied by high precise simulation of N-S（Navier-Stockes） equations. The Numerical results show good agreement with the experiments. It is indicated that the opposing jet is effective in reducing the aerodynamic heating and drag coefficient. Conclusions were got that the opposing jet enlarges the factors of affections by influencing the strength and the positions of the barrel shock, the mach disk and the recirculation region. It is believed that the drag coefficient turns out to be very sensitive to the flow field＇s structure which is highly depended on the free mach number, jet mach number and attack angle due to the opposing jet.

关 键 词：反向喷流 高超声速 阻力 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]