Analysis of Steady Cross-flow Instability Transition in Infinite Swept Wing Boundary Layer

doi:10.19596/j.cnki.1001-246x.7830

Abstract

Abstract: γ-Re_θt crossflow extension model was applied to conduct numerical simulation of crossflow transition on NLF(2)-0415 infinite swept wing. Effects of Reynolds number, surface roughness, sweep angle on crossflow instability of 3-D boundary layer were studied mainly. It found that γ-Re_θt crossflow extension model predicts 3-D boundary layer transition correctly and calculation results agree well with experiment data. It shows that with increase of Reynolds number or surface roughness, location of crossflow transition onset moves forward. However, with increase of sweep angle, location of crossflow transition onset moves forward firstly and then moves back.

Key words: swept wing, boundary layer, crossflow transition, k-ω SST turbulence model, γ-Re_θt transition model

CLC Number:

V211.3

CAI Linfeng, LI Haoge, CHEN Weifang. Analysis of Steady Cross-flow Instability Transition in Infinite Swept Wing Boundary Layer[J]. CHINESE JOURNAL OF COMPUTATIONAL PHYSICS, 2019, 36(2): 175-181.

References

[1] 周恒, 赵耕夫. 流动稳定性[M]. 北京:国防工业出版社, 2004:77-78.
[2] 徐国亮, 符松. 可压缩横流失稳及其控制[J]. 力学进展, 2012, 42(3):262-273.
[3] RONALD D. J. Overview of laminar flow control[J]. Experiments in Fluids, 1998:3-7.
[4] CHEN Y, TANG Z, SHENG J. Multi-objective optimization for natural laminar flow airfoil in transonic flow[J]. Chinese Journal of Computational Physics, 2016, 33(3):283-296.
[5] BOLTZ F W, KENYON G C, ALLEN C Q. Effects of sweep angle on the boundary-layer stability characteristics of an untapered wing at low speeds[R]. National Aeronautics and Space Administration, NASA Technical Note, 1960:D-338.
[6] HAYNES T S. Nonlinear stability and saturation of crossflow vortices in swept-wing boundary layers[D]. Arizona:Arizona State University, 1996.
[7] LANGTRY R B, SENGUPTA K, YEH D T, et al. Extending the γ-Re_θt local correlation based transition model for crossflow effects[R]. AIAA 2015-2474, Dallas, 2015.
[8] 杨永, 左岁寒, 李喜乐, 等. 基于升华法实验研究后掠翼三维边界层的转捩[J]. 实验流体力学, 2009, 23(3):40-43.
[9] LUO J, ZHOU H. A theoretical investigation of the development of stationary crossflow vortices in the boundary layer on a swept wing[J]. Acta Mechanica Sinica, 1998, 14(2):97-103.
[10] 左岁寒, 杨永, 李栋, 等. 基于线化稳定性理论的后掠翼边界层内横流稳定性研究[J]. 航空计算技术, 2009, 39(4):34-36.
[11] 徐家宽, 白俊强, 乔磊, 等. 后掠翼边界层横流不稳定转捩预测模型[J]. 航空动力学报,2015, 30(4):927-935.
[12] 徐家宽, 白俊强, 乔磊, 等. 横流不稳定性转捩预测模型[J]. 航空学报, 2015, 36(6):1814-1822.
[13] 史亚云, 白俊强, 华俊, 等. 基于当地变量的横流转捩预测模型的研究与改进[J]. 航空学报, 2016, 37(3):780-789.
[14] 鞠胜军, 阎超, 叶志飞. γ-Re_θt-CF转捩模型在Spalart-Allmaras湍流模型中的推广及验证[J]. 航空学报, 2017(4):71-79.
[15] 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.
[16] RAY D J, SARIC W S. Crossflow stability and transition experiments in swept-wing flow[R]. Hampton, USA:NASA Langley Research Center, TP-1999-209344, 1999.
[17] LI J, ZHANG L, YU J, et al. Study of rough wall heat flux in hypersonic turbulent flow[J]. Chinese Journal of Computational Physics, 2017, 34(2):165-174.