基于IDDES框架的γ-Reθ转捩模型

doi:10.7527/S1000-6893.2018.22726

流体力学与飞行力学

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基于IDDES框架的γ-Re_θ转捩模型

易淼荣, 赵慧勇, 乐嘉陵, 肖保国, 郑忠华

中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室, 绵阳 621000

收稿日期:2018-10-15 修回日期:2018-11-02 出版日期:2019-08-15 发布日期:2018-12-24
通讯作者: 赵慧勇 E-mail:gmreszhao@163.com
基金资助:
国家自然科学基金（51676204）；中国空气动力研究与发展中心风雷青年创新基金（PJD20170134）

γ-Re_θ transition model based on IDDES frame

YI Miaorong, ZHAO Huiyong, LE Jialing, XIAO Baoguo, ZHENG Zhonghua

Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2018-10-15 Revised:2018-11-02 Online:2019-08-15 Published:2018-12-24
Supported by:
National Natural Science Foundation of China (51676204);FengLei Youth Innovation Fund of CARDC (PJD20170134)

摘要/Abstract

摘要： 针对高超声速流动的γ-Re_θ转捩模型在模拟强制转捩时存在捕获边界层内扰动不足的缺点，将RANS（Reynolds Averaged Navier-Stokes）框架改为IDDES（Improved Delayed Detached Eddy Simulation）框架，既能像基于RANS框架的转捩模型一样模拟复杂构型的自然转捩，又能发挥IDDES能够捕获更多脉动信息的优点，较为准确地模拟粗糙颗粒诱导强制转捩。通过对一系列简单构型的自然转捩及来流马赫数为6条件下平板上单个粗糙颗粒诱导强制转捩的模拟表明，模型既能体现γ-Re_θ转捩模型的优点，在自然转捩模拟中具有较强的鲁棒性，能够反映雷诺数等因素对转捩位置的影响规律；也能体现IDDES方法的优点，能够捕捉粗糙颗粒诱导的扰动及涡结构，从而较为准确地刻画出强制转捩的整个流程。

关键词: 转捩模型, IDDES, 高超声速, 自然转捩, 强制转捩

Abstract: The improved γ-Re_θ transition model for hypersonic flow has the disability of capturing the disturbances in forced transition. To solve the problem, the RANS (Reynolds Averaged Navier-Stokes) framework is modified to IDDES (Improved Delayed Detached Eddy Simulation)frameworks. The new method can not only simulate the natural transition in the γ-Re_θ model but also simulate the forced transition process precisely by capturing more details in disturbances in the IDDES methods. The results of a series of natural transition of simple geometry cases and the roughness induced transition in a Mach number 6 flat plate show that the new method has the advantages of both the γ-Re_θ model and the IDDES methods. When simulating the natural transition, the influence rules on transition of important parameters such as Reynolds number and leading edge radius could be correctly reflected. When simulating the forced transition, the formation, development, and breakdown processes of the streamwise vortexes induced by the roughness element could be also captured.

Key words: transition model, IDDES, hypersonic, natural transition, forced transition

中图分类号:

V211.73

易淼荣, 赵慧勇, 乐嘉陵, 肖保国, 郑忠华. 基于IDDES框架的γ-Re_θ转捩模型[J]. 航空学报, 2019, 40(8): 122726-122726.

YI Miaorong, ZHAO Huiyong, LE Jialing, XIAO Baoguo, ZHENG Zhonghua. γ-Re_θ transition model based on IDDES frame[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(8): 122726-122726.

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[38]	TIRTEY S C, CHAZOT O, WALPOT L. Characterization of hypersonic roughness-induced boundary-layer transition[J]. Experiments in Fluids, 2011,50(2):407-418.
[19]	YI M R, ZHAO H Y, LE J L. Hypersonic natural and forced transition simulation by correlation-based intermittency model:AIAA-2017-2337[R]. Reston, VA:AIAA, 2017.
[20]	易淼荣,赵慧勇,乐嘉陵. 基于γ-Reθ转捩模型的高超声速复杂构型转捩模拟[J]. 实验流体力学, 2018, 32(4):1-11. YI M R, ZHAO H Y, LE J L. Hypersonic boundary layer transition simulation of complex configuration using γ-Reθtransition model[J].Journal of Experiments in Fluid Mechanics, 2018, 32(4):1-11(in Chinese).
[39]	TIRTEY S C, CHAZOT O.Characterization of hypersonic roughness induced transition for the EXPERT flight experiment:AIAA-2009-7215[R]. Reston, VA:AIAA, 2006.
[21]	CHEN X, ZHU Y, LEE C.Interactions between second mode and low-frequency waves in a hypersonic boundary layer[J]. Journal of Fluid Mechanics, 2017, 820:693-735.
[22]	潘翀, 王晋军. 自由来流扰动引起的旁路转捩研究进展[J]. 力学进展, 2011, 41(6):668-685. PAN C, WANG J J. Progress in bypass transition induced by free-stream disturbance[J]. Advances in Mechanics. 2011, 41(6):668-685(in Chinese).
[23]	YOON S, BARNHARDT M, CANDLER G. Simulations of high-speed flow over an isolated roughness:AIAA-2010-1573[R]. Reston, VA:AIAA, 2010.
[24]	DUAN Z W, XIAO Z X, FU S. Simulation of transition triggered by isolated roughness in hypersonic boundary layer:AIAA-2012-3076[R]. Reston, VA:AIAA, 2012.
[25]	XIAO L H, XIAO Z X, DUAN Z W, et al. Improved-delayed-detached-eddy simulation of cavity-induced transition in hypersonic boundary layer[J]. International Journal of Heat and Fluid Flow, 2015, 51:138-150.
[26]	BORG M P. Laminar instability and transition on the X-51A[D]. West Lafayette, IN:Purdue University, 2009:38-68.
[27]	SORENSEN N N, BECHMANN A, ZAHLE F. 3D CFD computations of transitional flows using DES and a correlation based transition model[J]. Wind Energy, 2011, 14(1):77-90.
[28]	ALAM M F, WALTERS D K, THOMPSON D S. A transition-sensitive hybrid RANS/LES modeling methodology for CFD applications:AIAA-2013-0995[R]. Reston, VA:AIAA, 2013.
[29]	WALTERS D K, COKLJAT D. A three-equation eddy-viscosity model for reynolds-averaged navier-stokes simulations of transitional flow[J]. ASME Journal of Fluids Engineering, 2008, 130(12):121401.
[30]	乔磊, 白俊强,华俊. Gamma-Theta经验转捩模型在DES中的应用[J]. 航空工程进展, 2013, 4(2):226-231. QIAO L, BAI J Q, HUA J.Application of Gamma-Theta transition model in DES[J]. Advances in Aeronautical Science and Engineering, 2013, 4(2):226-231(in Chinese).
[31]	赵慧勇.超燃冲压整体发动机并行数值研究[D]. 绵阳:中国空气动力研究与发展中心, 2005:41-97. ZHAO H Y.Massively parallel computation on scramjet combustor[D]. Mianyang:China Aerodynamics Research and Development Center,2005:41-97(in Chinese).
[32]	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 & Combustion, 2012, 88(3):431-449.
[33]	韩亦宇. 高超声速进气道激波振荡的DES数值模拟研究[D]. 绵阳:中国空气动力研究与发展中心, 2014:2-45. HAN Y Y. Detached Eddy Simulation(DES) of hypersonic inlet shock oscillation[D]. Mianyang:China Aerodynamics Research and Development Center, 2014:2-45(in Chinese).
[34]	GOEBEL S G. An experimental investigation of compressible turbulent mixing layers[D]. Urbana-Champaign, IL:University of Illinois, 1990:20-79.
[35]	FORSYTHE J R.Investigation of modified Menter's two-equation turbulence models for supersonic applications:AIAA-1999-0873[R]. Reston, VA:AIAA, 1999.
[36]	CHEN F J, MALIK M R. Boundary-Layer transition on a cone and flat plate at Mach 3.5[J]. AIAA Journal, 1989, 27(6):687-693.
[37]	NEUENHAHN T, OLIVIER H. Influence of the wall temperature and the entropy layer effects on double wedge shock boundary layer interactions:AIAA-2006-8136[R]. Reston, VA:AIAA, 2006.
[38]	TIRTEY S C, CHAZOT O, WALPOT L. Characterization of hypersonic roughness-induced boundary-layer transition[J]. Experiments in Fluids, 2011,50(2):407-418.
[39]	TIRTEY S C, CHAZOT O.Characterization of hypersonic roughness induced transition for the EXPERT flight experiment:AIAA-2009-7215[R]. Reston, VA:AIAA, 2006.

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基于IDDES框架的γ-Re_θ转捩模型

γ-Re_θ transition model based on IDDES frame

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基于IDDES框架的γ-Reθ转捩模型

γ-Reθ transition model based on IDDES frame

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基于IDDES框架的γ-Re_θ转捩模型

γ-Re_θ transition model based on IDDES frame