超声速小攻角下的圆锥转捩攻角效应  

Attack of angle effect for supersonic blunt cone transition flow

作　　者：潘宏禄[1] 马汉东[1] 沈清[1] 

机构地区：[1]航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2009年第1期97-101,共5页Acta Aerodynamica Sinica

摘　　要：采用高阶差分格式求解三维可压缩滤波Navier-Stokes方程,对超声速零攻角和小攻角圆锥边界层转捩进行了空间大涡模拟研究。在三维Tollmien-Schlichting(T-S)波扰动作用下,计算得到了流场非定常转捩过程。计算结果清晰地展现了非定常大尺度结构演化特征和攻角效应引起的非对称转捩现象,流场发卡涡、横流涡等转捩主控大尺度结构与实验一致。By large eddy simulation （LES） numerical method, the spatial transition coherent structures of a supersonic conic boundary layer at a free-stream Mach number of Ma= 3.5 based on free-stream velocity and a Reynolds number of Re=-20000/mm is studied with a hybrid method of a fifth-order upwind compact difference and a eighth-order symmetric compact difference for the three-dimensional compressible Favre- filtered Navier-Stokes equations. The sub-grid scales are formulated according to the modified Smagorinsky eddy-viscosity model. Based on the stability theory, a particular perturbation is introduced to the wall of inflow boundary and bypass transition is excitated. The computational results showed the evolution characters of unsteady large eddy in transition Well. Hairpin eddy and crossflow eddy are consistent with experiment data.

关 键 词：转捩 圆锥 可压缩边界层 大涡模拟 

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]