基于改进SST模型的分离流动数值模拟

推进技术 ›› 2013, Vol. 34 ›› Issue (5): 595-602.

基于改进SST模型的分离流动数值模拟

甘文彪,周洲,许晓平,王睿

西北工业大学无人机特种技术重点实验室,陕西西安 710072;西北工业大学无人机特种技术重点实验室,陕西西安 710072;西北工业大学无人机特种技术重点实验室,陕西西安 710072;西北工业大学无人机特种技术重点实验室,陕西西安 710072

发布日期:2021-08-15
作者简介:甘文彪(1985—),男,博士生,研究领域为计算流体力学与飞行器气动优化设计。E-mail:ganhope@126.com
基金资助:
国家装备预研基金(9140A25010312HK0301);国家自然基金(11202162)。

Investigation on Improving the Capability of Predicting Separation in Modified SST Turbulence Model

Science and Technology on UAV Laboratory, Northwestern Polytechnical University, Xi’an 710072, China;Science and Technology on UAV Laboratory, Northwestern Polytechnical University, Xi’an 710072, China;Science and Technology on UAV Laboratory, Northwestern Polytechnical University, Xi’an 710072, China;Science and Technology on UAV Laboratory, Northwestern Polytechnical University, Xi’an 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 对SST湍流模型进行了改进,并通过对典型分离流动进行数值模拟,来检验和提高模型预测分离流动的能力。基于亚声速分离流动,提出了提高雷诺应力的模拟精度和分离流修正的改进方法,并进行了对比研究得出结论；在亚声速分离流动分析结论基础上,采用了可压缩性修正方法,开展了跨声速、超声速和高超声速激波/边界层干扰分离流动的数值模拟研究。结果表明:提高雷诺应力的模拟精度和采用分离流修正明显地提高了SST湍流模型对分离流动的模拟能力；适当地可压缩性修正对超声速和高超声速分离流动的计算精度有改善作用。 

关键词: SST湍流模型;分离流;雷诺应力;可压缩性修正;激波/边界层干扰 

Abstract: To verify and improve the capability of predicting separation, SST turbulence model was modified and applied to simulate separation flows. Firstly, starting from the property of subsonic, Reynolds stress simulation improvement and separation correction were used, some significant conclusions were reached from comparison. Secondly, based on hypersonic and supersonic, the modified model employed compressibility correction and simulated shock wave/boundary-layer interaction in transonic, supersonic and hypersonic. Finally, the results show that Reynolds stress simulation improvement and separation correction can improve the capability of predicting separation and suitable compressibility correction obviously improves the capability of prediction supersonic and hypersonic separation flow.

Key words: SST turbulence model; Separation flow; Reynolds stresses; Compression modification; Shock wave /boundary-layer interaction

甘文彪,周洲,许晓平,王睿. 基于改进SST模型的分离流动数值模拟[J]. 推进技术, 2013, 34(5): 595-602.

GAN Wen-biao,ZHOU Zhou,XU Xiao-ping,WANG Rui. Investigation on Improving the Capability of Predicting Separation in Modified SST Turbulence Model[J]. Journal of Propulsion Technology, 2013, 34(5): 595-602.

参考文献

[1] Abid R, Rumsey C, Gatski T.Prediction of Nonequilibrium Turbulent Flows with Explicit Algebraic Stress Models [J].AIAA Journal, 1995,3(11):2026-2031.
[2] Menter F R．Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications [J].AIAA Journal, 1994,2(8):1598-1605.
[3] Wilcox D C．Formulation of the k-ω Turbulence Model Revisited [J].AIAA Journal,2008,46(11):2823-2838．
[4] 马威, 王丹华, 陆利蓬.提高Spalart-Allmaras湍流模型对分离模拟能力的研究[J].航空动力学报,2008,23(8):1474-1479.
[5] Krist S L, Biedron R T,Rumsey C L.CFL3D User’s Manual:Ver.5.0[R].NASA-TM 1998-208444.
[6] Gritskevich M S, Garbaruk A V, Schütze J,et al.Development of DDES and IDDES Formulations for the k-ω Shear Stress Transport Model [J].Flow Turbulence Combust,2012,(88):431-449.
[7] Zeman O.A New Model for Super/Hypersonic Turbulent Boundary Layers[R].AIAA 93-0897.
[8] Wilcox D C.Turbulence Modeling for CFD[C].Canada:DCW Industries Inc.,2006.
[9] Rumsey C, Sanetrik M, Biedron R,et al.Efficiency and Accuracy of Time-Accurate Turbulent Navier-Stokes Computations [J].Computers& Fluids, 1996; 25(2):217-236.
[10] 甘文彪,阎超.高超声速飞行器后体尾喷管优化设计[J].北京航空航天大学学报,2011,37(11):68-73.
[11] Rumsey C L.Proceedings of the 2004Workshop on CFD Validation of Synthetic Jets and Turbulent Separation Control[R].NASA/CP 2007-214874.
[12] Delery J M.Investigation of Strong Shock Turbulent Boundary Layer Interaction in 2-D Transonic Flows with Emphasis on Turbulence Phenomena[R].AIAA 81-1245.
[13] 谭杰,金捷.跨声速和超声速流中激波/边界层干扰数值模拟[J].推进技术,2010,31(4):394-400.(TAN Jie,JIN Jie．Numerical Simulation of Shock Wave /Turbulent Boundary-Layer Interactions in Transonic and Supersonic[J].Journal of Propulsion Technology, 2010,1(4):394-400.)
[14] Liou W W, Huang G, Shih T.Turbulence Model Assessment for Shock Wave/ Turbulent Boundary-Layer Interaction in Transonic and Supersonic Flows [J].Computers＆Fluids, 2000,9(6):275-299.
[15] Schmisser J D, Caitonde D V.Numerical Investigation of New Topologies in Strong Crossing Shock-Wave/Turbulent Boundary-Layer Interactions[R].AIAA 2000-0931.
[16] 金亮,梁剑寒,孙明波,等.交叉激波湍流边界层干扰问题数值模拟[J].国防科技大学学报,2008,30(3):11-14.