Improvement of shock wave and compressibility effects in SST turbulence model

被引：0

作者：

Wang H. ^{[1
]}

Zeng Y. ^{[1
]}

Xiong D. ^{[1
]}

Yang Y. ^{[1
]}

Sun M. ^{[1
]}

机构：

[1] Laboratory of Science and Technology on Scramjet, College of Aerospace Science, National University of Defense Technology, Changsha

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2024年 / 45卷 / 03期

基金：

中国国家自然科学基金;

关键词：

compressibility; shock wave; SST; structure characteristics; turbulence model;

D O I：

10.7527/S1000-6893.2023.28694

中图分类号：

学科分类号：

摘要：

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. © 2024 Chinese Society of Astronautics. All rights reserved.

引用

共 50 条

[31] SARKAR S., The pressure⁃dilatation correlation in com⁃ pressible flows［J］, Physics of Fluids A：Fluid Dynam⁃ ics, 4, 12, pp. 2674-2682, (1992)
[32] ZEMAN O., Dilatation dissipation：The concept and ap⁃ plication in modeling compressible mixing layers［J］, Physics of Fluids A：Fluid Dynamics, 2, 2, pp. 178-188, (1990)
[33] WILCOX D C., Dilatation-dissipation corrections for ad⁃ vanced turbulence models［J］, AIAA Journal, 30, 11, pp. 2639-2646, (1992)
[34] BROWN J., Turbulence model validation for hypersonic flows, Proceedings of the 8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, (2002)
[35] ZHAO G Y，, Et al., Effect of injec⁃ tion scheme on asymmetric phenomenon in rectangular and circular scramjets［J］, Chinese Journal of Aeronau⁃ tics, 36, 1, pp. 216-230, (2023)
[36] LIU M J, ZHAO G Y，, Et al., Effect of com⁃ bustion mode on thrust performance in a symmetrical tandem-cavity scramjet combustor［J］, Aerospace Sci⁃ ence and Technology, 130, (2022)
[37] ZHANG C, CHOUDHARI M M., Direct numerical simulation database for supersonic and hyper⁃ sonic turbulent boundary layers ［J］, AIAA Journal, 56, 11, pp. 4297-4311, (2018)
[38] Experimental study of a Mach 3 compression ramp in⁃ teraction at Re<sub>θ</sub> = 2400［J］, AIAA Journal, 47, 2, pp. 373-385, (2009)
[39] WU M, MARTIN M P., Direct numerical simulation of supersonic turbulent boundary layer over a compression ramp［J］, AIAA Journal, 45, 4, pp. 879-889, (2007)
[40] HOLDEN M S, MACLEAN M G., Measurements in regions of shock wave/turbulent bound⁃ ary layer interaction from Mach 4 to 10 for open and “Blind”code evaluation/validation［C］∥ Proceedings of the 21st AIAA Computational Fluid Dynamics Confer⁃ ence, (2013)

← 1 2 3 4 5 →