进气道中激波-边界层干扰特性研究  

Research on Shock-Boundary Layer Interaction in Hypersonic Inlets

作　　者：谭伟伟[1] 田增冬[1] 梁益华[1] 

机构地区：[1]中航工业西安航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2014年第1期41-44,共4页Aeronautical Computing Technique

基　　金：国家863计划项目资助(2012AA01A304)

摘　　要：针对高超进气道中激波/边界层干扰等现象,选取了24°压缩拐角及二维高超进气道DLR-GK01等算例,比较研究了混合网格并行数值模拟软件中SA、SST、TNT三种湍流模型对激波/边界层干扰等现象的模拟能力,主要考察了不同湍流模型对流场结构、壁面压强以及壁面摩阻的影响。结果表明:三种湍流模型在模拟大分离流场时存在不同的流动分离特性,TNT湍流模型较SST和SA湍流模型模拟的分离起始位置、分离区大小及边界层厚度与实验吻合度最好。This paper focus on the capability of turbulence model to capture shock- boundary layer inter- action phenomenon using hybrid grid based CFD solver. While doing this, we choose two test cases, which are compression comer with corner angle 24° and DLR- GK01 two dimensional hypersonic inlets, to eval- uate different turbulence model by comparing the simulated flow structure, pressure and friction coeffi- cient. The solutions show that compared to Menter SST turbulence model, SA and Kok＇s TNT turbulence model are more suitable for simulating those flows with shock- boundary layer interaction phenomenon.

关 键 词：NAVIER-STOKES方程 高超声速 激波 边界层干扰 DLR-GK01进气道 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]