应用γ-Reθ湍流模型和PSE方法研究高超声速流动  

Investigation on supersonic flow with γ-Reθ turbulence model and PSE methodinvestigation on supersonic flow

作　　者：颜培刚[1] 董学智[1] 韩万金[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：《航空动力学报》2010年第6期1284-1290,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(50706009)

摘　　要：采用考虑转捩的γ-Reθ湍流模型研究了高超声速复杂流动,结合PSE(parabolic stability equa-tion)稳定性分析方法和e-N方法,通过给出边界层最不稳定点的参数,用以控制γ-Reθ的转捩经验关联式,减少对经验参数的依赖.计算了锥体高超声速流场,得到的壁面换热量和边界层转捩位置与实验吻合较好.计算了平板激波/边界层干扰和高超声速拐角压缩流场,得到了准确的波系结构、压力分布和分离区的大小.结果表明,该方法与传统湍流模型相比具有较大的优越性.The γ-Reθ turbulence model involved with empirical correlation for transition was adopted to investigate the typical hypersonic flows.Parabolic stability equation（PSE） stability analysis and e-N prediction methods were combined to find the most unstable point of boundary layer,showing that the transition empirical correlation parameters were more appropriate,with less dependency on design experiences.The hypersonic flow field of a blunt cone was simulated,and the computational wall heat flux and boundary layer transition position were consistent well with the experimental results.The shock wave/flat plat interaction and the flow across a compression corner were computed.The analysis of shock wave structure and separated flow shows that the model is also applicable for simulation of complicated flow with shock wave/boundary layer interaction.The results show that the method of this paper is superior to the traditional turbulence models.

关 键 词：高超声速 PARABOLIC stability equation(PSE)稳定性方程 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]