适用于可压缩流动的γ-Reθt-fRe转捩模型

刘清扬; 雷娟棉; 刘周; 石磊; 周伟江

doi:10.7527/S1000-6893.21.25794

航空学报 >

2022 , Vol. 43 >Issue 8: 125794 - 125794

DOI: https://doi.org/10.7527/S1000-6893.21.25794

流体力学与飞行力学

适用于可压缩流动的γ-Re_θt-f_Re转捩模型

刘清扬 ,
雷娟棉 ,
刘周 ,
石磊 ,
周伟江

展开

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

收稿日期: 2021-05-13

修回日期: 2021-07-22

网络出版日期: 2022-09-05

基金资助

国家数值风洞工程;国家自然科学基金(11772317)

收起

γ-Re_θt-f_Re transition model for compressible flow

LIU Qingyang ,
LEI Juanmian ,
LIU Zhou ,
SHI Lei ,
ZHOU Weijiang

Expand

1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
2. China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received date: 2021-05-13

Revised date: 2021-07-22

Online published: 2022-09-05

Supported by

National Numerical Windtunnel Project;National Natural Science Foundation of China (11772317)

Fold

摘要

基于γ-Re_θt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f_Re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f_Re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-Re_θt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-Re_θt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。

关键词： 流动转捩; 高超声速; γ-Re_θt转捩模型; 参考温度法; 可压缩性修正

本文引用格式

刘清扬 , 雷娟棉 , 刘周 , 石磊 , 周伟江 . 适用于可压缩流动的γ-Re_θt-f_Re转捩模型[J]. 航空学报, 2022 , 43(8) : 125794 -125794 . DOI: 10.7527/S1000-6893.21.25794

Abstract

A transition model, γ-Re_{θ t}-f_Re, considering flow compressibility is developed from the original γ-Re_{θ t}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 f_Re transport equation is constructed. The developed γ-Re_{θ t}-f_Re transition model is used to examine the transition cases under different flow conditions and compared with the basic γ-Re_{θ t} transition model. The numerical simulation results show that the γ-Re_{θ t}-f_Re transition model achieves seamless unified simulation capability from low speed to high speed. It is automatically restored to the basic γ-Re_{θ t} 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.

Key words： flow transition; hypersonic; γ-Re_{θ t} transition model; reference temperature method; compressibility correction

参考文献

[1] 陈苏宇, 江涛, 常雨, 等. 高超声速钝头体边界层转捩试验[J]. 航空学报, 2020, 41(12): 124098. CHEN S Y, JIANG T, CHANG Y, et al. Hypersonic boundary layer transition over blunt nosetipped bodies: Experiment[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(12): 124098 (in Chinese).
[2] 袁湘江, 沙心国, 时晓天, 等. 高超声速流动中噪声与湍流度的关系[J]. 航空学报, 2020, 41(11): 123791. YUAN X J, SHA X G, SHI X T, et al. Noise-turbulence relationship in hypersonic flow[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(11): 123791 (in Chinese).
[3] 陈坚强, 涂国华, 万兵兵, 等. HyTRV流场特征与边界层稳定性特征分析[J]. 航空学报, 2021, 42(6): 124317. CHEN J Q, TU G H, WAN B B, et al. Characteristics of flow field and boundary-layer stability of HyTRV[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 124317 (in Chinese).
[4] LANGTRY R B, MENTER F R. Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes[J]. AIAA Journal, 2009, 47(12): 2894-2906.
[5] LANGTRY R B, SENGUPTA K, YEH D T, et al. Extending the γ-Re_θt local correlation based transition model for crossflow effects: AIAA-2015-2474[R]. Reston: AIAA, 2015.
[6] WALTERS D K, LEYLEK J H. A new model for boundary layer transition using a single-point RANS approach[J]. Journal of Turbomachinery, 2004, 126(1): 193-202.
[7] MENTER F R, SMIRNOV P E, LIU T, et al. A one-equation local correlation-based transition model[J]. Flow, Turbulence and Combustion, 2015, 95(4): 583-619.
[8] CODER J G. Enhancement of the amplification factor transport transition modeling framework: AIAA-2017-1709[R]. Reston: AIAA, 2017.
[9] 张毅锋, 何琨, 张益荣, 等. Menter转捩模型在高超声速流动模拟中的改进及验证[J]. 宇航学报, 2016, 37(4): 397-402. ZHANG Y F, HE K, ZHANG Y R, et al. Improvement and validation of menter’s transition model for hypersonic flow simulation[J]. Journal of Astronautics, 2016, 37(4): 397-402 (in Chinese).
[10] 袁先旭, 何琨, 陈坚强, 等. MF-1模型飞行试验转捩结果初步分析[J]. 空气动力学学报, 2018, 36(2): 286-293. YUAN X X, HE K, CHEN J Q, et al.Preliminary transition research analysis of MF-1[J]. Acta Aerodynamica Sinica, 2018, 36(2): 286-293 (in Chinese).
[11] KRAUSE M, BEHR M, BALLMANN J. Modeling of transition effects in hypersonic intake flows using a correlation-based intermittency model: AIAA-2008-2598[R]. Reston: AIAA, 2008.
[12] ZHANG X D, GAO Z H. A numerical research on a compressibility-correlated langtry’s transition model for double wedge boundary layer flows[J]. Chinese Journal of Aeronautics, 2011, 24(3): 249-257.
[13] XIA C C, CHEN W F. Boundary-Layer transition prediction using a simplified correlation-based model[J]. Chinese Journal of Aeronautics, 2016, 29(1): 66-75.
[14] FRAUHOLZ S, REINARTZ B U, MüLLER S, et al. Transition prediction for scramjets using γ-Re_{θ t} model coupled to two turbulence models[J]. Journal of Propulsion and Power, 2015, 31(5): 1404-1422.
[15] WANG Y T, LI Y W, XIAO L H, et al. Similarity-solution-based improvement of γ-Re_{θ t} model for hypersonic transition prediction[J]. International Journal of Heat and Mass Transfer, 2018, 124: 491-503.
[16] FU S, WANG L. RANS modeling of high-speed aerodynamic flow transition with consideration of stability theory[J]. Progress in Aerospace Science, 2012, 58: 36-59.
[17] WANG L, FU S. Development of an intermittency equation for the modeling of the supersonic/hypersonic boundary layer flow transition[J]. Flow, Turbulence and Combustion, 2011, 87(1): 165-187.
[18] 周玲, 阎超, 郝子辉, 等. 转捩模式与转捩准则预测高超声速边界层流动[J]. 航空学报, 2016, 37(4): 1092-1102. ZHOU L, YAN C, HAO Z H, et al. Transition model and transition criteria for hypersonic boundary layer flow[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(4): 1092-1102 (in Chinese).
[19] XU J K, BAI J Q, FU Z Y, et al. Parallel compatible transition closure model for high-speed transitional flow[J]. AIAA Journal, 2017, 55(9): 3040-3050.
[20] SHI M T, ZHU W K, LEE C B. Engineering model for transition prediction based on a hypersonic quiet wind tunnel[J]. AIAA Journal, 2020, 58(8): 3476-3485.
[21] 易淼荣, 赵慧勇, 乐嘉陵, 等. 基于IDDES框架的 γ-Re_θ 转捩模型[J]. 航空学报, 2019, 40(8): 122726. YI M R, ZHAO H Y, LE J L, et al . γ-Re_θ transition model based on IDDES frame[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(8): 122726 (in Chinese).
[22] ECKERT E R G. Engineering relations for heat transfer and friction in high-velocity laminar and turbulent boundary-layer flow over surfaces with constant pressure and temperature[J]. Transactions of the American Society of Mechanical Engineers, 1956, 78(6): 1273.
[23] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605.
[24] NIE S Y, KRIMMELBEIN N, KRUMBEIN A, et al. Coupling of a Reynolds stress model with γ-Re_{θ t} transition model[J]. AIAA Journal, 2018, 56(1): 146-157.
[25] MEE D. Boundary-layer transition measurements in hypervelocity flows in a shock tunnel[J]. AIAA Journal, 2002, 40(8): 1542-1548.
[26] CHEN F, MALIK M R, BECKWITH I E. Boundary-layer transition on a cone and flat plate at Mach 3.5[J]. AIAA Journal, 1989, 27(6): 687-693.
[27] SINGER B A, DINAVAHI S P, VENKIT I. Testing of transition-region models: test cases and data: NASA CR 4371[R]. Washington, D.C.: NASA, 1991.
[28] 刘周, 龚安龙, 杨云军, 等. 基于 γ-Re_θ 转捩模型的尖锥超声速流动转捩模拟[C]//第十七届全国高超声速气动力/热学术交流会, 2013. LIU Z, GONG A L, YANG Y J, et al. Supersonic flow transition simulations of sharp cone using γ-Re_θ transition model[C]//17th National Hypersonic Aerodynamics/Heat Symposium Proceeding, 2013 (in Chinese).
[29] HORVATH T J, BERRY S A, HOLLIS B R, et al. Boundary layer transition on slender cones in conventional and low disturbance Mach 6 wind tunnels: AIAA-2002-2743[R]. Reston: AIAA, 2002.

Options

文章导航

模态框（Modal）标题

摘要

本文引用格式

Abstract

参考文献