适用于可压缩流动的γ-Re_(θt)-f_(Re)转捩模型  

γ-Re_(θt)-f_(Re) transition model for compressible flow

作　　者：刘清扬 雷娟棉 刘周[2] 石磊[2] 周伟江[2] LIU Qingyang;LEI Juanmian;LIU Zhou;SHI Lei;ZHOU Weijiang(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]中国航天空气动力技术研究院,北京100074

出　　处：《航空学报》2022年第8期321-331,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家数值风洞工程;国家自然科学基金(11772317)。

摘　　要：基于γ-R_(eθt)转捩模型的框架,发展了考虑流动可压缩性的γ-Re_(θt)-f_(Re)转捩模型。针对已有的转捩准则引入可压缩性修正,并利用基于参考温度法获得的雷诺数可压缩性比拟关系fRe修正现有基于不可压缩流动的转捩关联函数。为实现模型的局部性,构建了额外的雷诺数可压缩性比拟关系fRe输运方程。利用所发展的γ-Re_(θt)-f_(Re)转捩模型对不同流动条件的转捩算例进行考核并和基本γ-R_(eθt)转捩模型进行对比,结果显示,γ-Re_(θt)-f_(Re)转捩模型实现了从低速至高速的无缝统一模拟能力。在低速流动条件下,γ-Re_(θt)-f_(Re)转捩模型自动恢复为基本γ-R_(eθt)转捩模型;在超声速和高超声速流动条件下,γ-Re_(θt)-f_(Re)转捩模型显著改善了流动转捩的起始位置和转捩区发展的预测。A transition model,γ-Re_(θt)-f_(Re),considering flow compressibility is developed from the originalγ-R_(eθt)transition model framework.The compressibility correction is introduced for the existing transition criteria,and the original transition correlation function based on incompressible flow is modified using the Reynolds number compressibility analogy relation obtained by the reference temperature method.To achieve model localization,an additional Reynolds number compressibility analogy relation fRe transport equation is constructed.The developedγ-Re_(θt)-f_(Re) transition model is used to examine the transition cases under different flow conditions and compared with the basicγ-R_(eθt) transition model.The numerical simulation results show that theγ-Re_(θt)-f_(Re) transition model achieves seamless unified simulation capability from low speed to high speed.It is automatically restored to the basicγ-R_(eθt) transition model under low speed flow conditions,while significantly improves the prediction of the flow transition trigger position and transition zone development under supersonic and hypersonic flow conditions.

关 键 词：流动转捩 高超声速 γ-R_(eθt)转捩模型 参考温度法 可压缩性修正 

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]