高超声速双椭球气动热环境预测  

Prediction of Aero-Heating Environment of the Hyper-Sonic Double Ellipsoid Flow

作　　者：朱志斌[1] 尚庆[1] 潘宏禄[1] 姜宝森 ZHU Zhibin;SHANG Qing;PAN Honglu;JIANG Baosen(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,北京100074

出　　处：《兵器装备工程学报》2019年第1期111-117,共7页Journal of Ordnance Equipment Engineering

摘　　要：采用不同数值模拟方法,对双椭球外形高超声速绕流的气动热环境进行了模拟预测,对比分析了计算网格、数值格式、湍流模型等对计算结果的影响。数值模拟表明,双椭球超声速绕流在相贯线附近会发生激波与边界层干扰,引起分离旋涡并诱发流动转捩,从而改变边界层流动状态,并直接影响热流分布。层流和全湍流计算得到的热流分布与实验数据存在偏差,而转捩模式能够更为准确地预测热流分布;大涡模拟捕捉到了分离诱导转捩的时空发展过程,发现流场涡系结构的发展演化与热流分布具有直接相关性。The flow field around the double ellipsoid model was simulated by using different numerical methods.The effects of grid resolution,scheme orders and RANS models on the aero-heating distributions were analyzed.The numerical results show that the shock boundary layer interaction occurs near the connecting line of the two ellipsoids,and the separated vortex induces the transition of boundary layer,which stirs up aero-heating distribution directly.The heat flux distribution of laminar flow and total turbulence is deviant from the experimental data,and the transition model can predict the aero heat more accurately.The large eddy simulation captures the temporal and spatial evolution of the separation induced transition,which reveals that the evolution of the vortex structure has direct correlation with the heat flux distribution.

关 键 词：高超声速 双椭球 气动热 转捩、湍流 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]