摘要
以光学窗口的气动光学效应研究为背景,研究影响光学传输预测的流场湍流脉动量预测.选取平板、压缩拐角、凹腔流动模型,采用大涡模拟（LES）方法研究超声速湍流脉动工程预测模型的系数修正.结果表明：LES方法能够获得无激波干扰、强激波干扰及底部大分离条件下,湍流密度脉动的定量分布,并据此给出脉动工程模型的系数修正,结果已经应用于型号飞行器的光学窗口气动光学效应预测.
Aero-optic effect is investigated in supersonic/hypersonic flow. Flat plate,ramp and cave model in supersonic/hypersonic flow condition are studied with large eddy simulation（LES）. Turbulent density pulse is predicted to verify coefficient of density pulse model-mixing length（ML） model. It indicates that LES method simulates turbulent density pulse well in flat plate boundary layer flow,oblique shock wave/boundary layer interaction and strong separation flow. Density pulse data obtained by LES is used to verify ML coefficient and set a quantitative result. The modified ML was used to predict aero-optical effect on missile successfully.
作者
潘宏禄
李俊红
程晓丽
马汉东
PAN Honglu;LI Junhong;CHENG Xiaoli;MA Handong(China Academy of Aerospace Aerodynamics, Beijing 100074, China)
出处
《计算物理》
EI
CSCD
北大核心
2018年第2期194-204,共11页
Chinese Journal of Computational Physics
基金
国家自然基金(1102199,11402254)资助项目
关键词
气动光学效应
湍流
超声速边界层
分离流动
大涡模拟
aero-optic
turbulence
supersonic boundary layer
separation flow
large eddy simulation
