高超飞行器内流道激波振荡问题的数值研究及试验验证  

Numerical simulation and experiment validation on shock oscillations of inner flow path of hypersonic vehicle

作　　者：郭善广[1] 柳军[1] 金亮[1] 罗世彬[1] 

机构地区：[1]国防科学技术大学高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《实验流体力学》2012年第1期7-11,共5页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金资助项目(90816027)

摘　　要：采用数值模拟和风洞试验的方法,对吸气式高超声速飞行器盲腔状态的流动特性进行了研究。采用'双时间步'方法进行了内外流一体化的非定常数值模拟,利用彩色纹影系统对高超声速飞行器前体流场进行显示,并采用动态压力传感器测得了飞行器内流道的壁面压力随时间的变化。结果表明:盲腔构型在高超声速飞行中会出现周期性的激波振荡现象。数值模拟所得流场变化特征、内流道壁面压力振荡周期和壁面压力变化趋势与试验结果吻合良好。An analysis was conducted for the flow characteristic of the axisymmetric air-breathing hypersonic vehicle under blind cavity with numerical simulations and wind tunnel tests.The dual-time-step scheme was used to simulate the integrated flow field of the hypersonic vehicle.The color schlieren technique was used to visualize forebody flow of the vehicle.Furthermore,transient pressure sensors were used to record the wall pressure of the inner flow path.The result demonstrated that shock oscillations appeared in the inner flow path of the vehicle during boosting flight.The CFD results were compared with experiment data and showed good agreement in flow field characteristic,pressure oscillation period and changing trend of the wall pressure.

关 键 词：高超声速飞行器 数值模拟 试验验证 非定常流 激波振荡 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]