表面热膜在高超声速边界层中的应用  

EXPERIMENTAL STUDY OF HYPERSONIC BOUNDARY LAYERS FLOW WITH SURFACE HOT-FILM

作　　者：顾蕴松[1] 明晓[1] 

机构地区：[1]南京航空航天大学空气动力学系,南京210016

出　　处：《宇航学报》2001年第6期102-105,123,共5页Journal of Astronautics

摘　　要：本文针对标准 1 0°圆锥在不同攻角下边界层的转捩和流动分离现象进行了试验研究。在高超声速情况下 ,应用表面热膜试验技术测得了 1 0°圆锥在不同攻角下的壁面摩擦应力和动态信号数据。试验研究结果表明表面热膜技术可以成功地应用到高超声速的边界层研究中。所得到的数据有助于正确理解高超声速的边界层的特性。特别是驻点线上 。Research was conducted on the experimentally study of the three dimensional boundary layers transition and separation phenomena on a 10 degrees cone model in hypersonic flow.The wind tunnel model,for the purpose of investigation of 3 D boundary layers characteristic,a stainless 10 degrees cone model was especially designed.With surface hot film technique,the boundary layer transition and separation were determined by means of wall shear stress measurements at varies attack angle.The result showed clearly the transition region and separation region on the cone model.A set of dynamic data was yielded and it can be used in the evaluation and improvement of dynamic flow quality of the wind tunnel in which these experiments were performed.

关 键 词：10°圆锥 表面热膜 高超声速边界层转捩 滚动分离 计算空气动力学 风洞实验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]