应用γ-Re_θ湍流模型模拟超声速进气道流动  

Simulation of flow field in a supersonic inlet by γ-Re_θ turbulence model

作　　者：颜培刚[1] 韩万金[1] 严红明[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《哈尔滨工业大学学报》2011年第1期95-98,共4页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金资助项目(50706009)

摘　　要：为了准确预估转捩起始点位置,采用考虑转捩的γ-Reθ湍流模型,对锥体高超声速流场和平板激波/边界层干扰流场进行了验证,有效地预测了边界层转捩位置、激波/边界层干扰的复杂波系结构、分离流动以及气动加热现象,且比传统的湍流模型具有更高的可信度.设计了三压缩角和等熵压缩型面进气道流场,计算结果表明,等熵压缩型面设计具有较好的喉部通流能力和较高的总压恢复性能,在进气道喉部之后,两方案性能基本一致.To improve the prediction of transition, the γ-Reθ turbulence model involved with empirical correlations for transition prediction is used to analyze two typical hypersonic flow fields of the blunt cone and the fiat plat shock wave/boundary layer interaction, and the computational results agree well with ＇the experimental results, which show that the turbulence transition model adopted in this paper has a higher credibility than traditional turbulence models. Furthermore, two supersonic inlets with triple-compression angle and isentropic compression profile are designed and simulated, respectively. The results show that the isentropic compression profile has better throat flow capability and higher total pressure recovery performance and the aerodynamic performances at the rear part of the throat section are almost the same for the two cases.

关 键 词：超声速流动 湍流模型 转捩 激波 边界层 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]