气动光学效应湍流脉动模型系数修正  

Model Coefficient Revision on Supersonic Turbulent Pulse for Aero-Optic Effect

作　　者：潘宏禄[1] 李俊红[1] 程晓丽[1] 马汉东[1] PAN Honglu;LI Junhong;CHENG Xiaoli;MA Handong(China Academy of Aerospace Aerodynamics, Beijing 100074, China)

机构地区：[1]中国航天空气动力技术研究院

出　　处：《计算物理》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

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.

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 

分 类 号：O357.5[理学—流体力学] V211.3[理学—力学]