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| 进气道中激波-边界层干扰特性研究 | |
| 引用本文： | 谭伟伟,田增冬,梁益华. 进气道中激波-边界层干扰特性研究[J]. 航空计算技术, 2014, 0(1): 41-44 |
| 作者姓名： | 谭伟伟 田增冬 梁益华 |
| 作者单位： | 中航工业西安航空计算技术研究所,陕西西安710068 |
| 基金项目： | 国家863计划项目资助（2012AA01AS04） |
| 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。 |
| 关 键 词： | Navier-Stokes方程 高超声速 激波/边界层干扰 DLR-GK进气道 |
Research on Shock- Boundary Layer Interaction in Hypersonic Inlets |
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| Affiliation: | TAN Wei- wei, TIAN Zeng- dong, LIANG Yi- hua ( Xi＇an Aeronautics Computing Technique Research Institute ,A VIC,Xi＇an 710068, China) |
| Abstract: | 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. |
| Keywords: | Navier- Stokes equetions hypersonic flow shock- boundary layer interaction DLR- GK01 inlet |
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