SST湍流模型的激波与可压缩效应改进  

Improvement of shock wave and compressibility effects in SST turbulence model

作　　者：汪洪波[1] 曾宇 熊大鹏 杨揖心 孙明波[1] WANG Hongbo;ZENG Yu;XIONG Dapeng;YANG Yixin;SUN Mingbo(Laboratory of Science and Technology on Scramjet,College of Aerospace Science,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院、高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《航空学报》2024年第3期91-104,共14页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11925207,T2221002)。

摘　　要：由于缺乏对某些重要流动特征的考虑,针对不可压流发展的标准SST湍流模型在描述超声速流场时存在明显的局限性。为改善SST模型在吸气式高超声速推进系统内流等复杂超声速流场中的预测精度,基于流动特征结构定向开展了激波和可压缩效应改进。通过激波/湍流边界层判别函数和可压缩效应判别函数定位标准SST模型参数或建模假设失效的区域,针对性地改进湍流模型。采用超声速平板边界层流动、超声速压缩拐角分离流动、超声速隔离段复杂激波串流动以及HIFiRE-2超声速内流等算例进行了测试,结果表明改进模型具有与标准SST模型一致的边界层预测能力,但显著提高了对激波干扰流动及逆压分离流的预测精度。Lack of consideration of certain important flow characteristics leads to obvious limitations in supersonic flow description by the standard SST turbulence model developed for incompressible flow.To improve the prediction accu⁃racy of the SST model in complex supersonic flows involved in hypersonic propulsion systems,the shock wave and compressibility effects were introduced based on the flow characteristics.The shock/turbulent boundary layer discrimi⁃nant function and compressible effect discriminant function were used to locate the region where the model parameters or modeling assumptions of the standard SST model failed,and the turbulence model was improved directionally.Ex⁃amples of supersonic plate boundary layer flow,supersonic compression corner separation flow,supersonic complex shock train flow in an isolator and HIFiRE-2 supersonic internal flow were used for testing.The results show that the improved model has the same prediction ability as the standard SST model for turbulent boundary layers,but signifi⁃cantly improves the prediction ability of shock-wave involved flows and adverse-pressure-gradient induced separating flows.

关 键 词：SST 湍流模型 激波 可压缩 结构特征 

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]