Numerical study of compression corner flowfield using Gao-Yong turbulence model

GAO Ge; ZHANG Chang-xian; YAN Wen-hui; WANG Yong

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Numerical study of compression corner flowfield using Gao-Yong turbulence model

气动热力学与总体设计 | 更新时间：2026-07-07

- Numerical study of compression corner flowfield using Gao-Yong turbulence model
- Numerical study of compression corner flowfield using Gao-Yong turbulence model
- 航空动力学报 2012年27卷第1期
- 作者机构：
  
  1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing,China,100091
  2. Chinese Aeronautical Establishment,Beijing,China,100012
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- 纸质出版：2012
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GAO Ge, ZHANG Chang-xian, YAN Wen-hui, 等. Numerical study of compression corner flowfield using Gao-Yong turbulence model[J]. 航空动力学报, 2012,27(1).

GAO Ge, ZHANG Chang-xian, YAN Wen-hui, et al. Numerical study of compression corner flowfield using Gao-Yong turbulence model[J]. 2012, 27(1).
GAO Ge, ZHANG Chang-xian, YAN Wen-hui, 等. Numerical study of compression corner flowfield using Gao-Yong turbulence model[J]. 航空动力学报, 2012,27(1). DOI：

GAO Ge, ZHANG Chang-xian, YAN Wen-hui, et al. Numerical study of compression corner flowfield using Gao-Yong turbulence model[J]. 2012, 27(1). DOI：

摘要

A numerical simulation of shock wave turbulent boundary layer interaction induced by a 24° compression corner based on Gao-Yong compressible turbulence model was presented.The convection terms and the diffusion terms were calculated using the second-order AUSM (advection upstream splitting method) scheme and the second-order central difference scheme

respectively.The Runge-Kutta time marching method was employed to solve the governing equations for steady state solutions.Significant flow separation-region which indicates highly non-isotropic turbulence structure has been found in the present work due to intensity interaction under the 24° compression corner.Comparisons between the calculated results and experimental data have been carried out

including surface pressure distribution

boundary-layer static pressure profiles and mean velocity profiles.The numerical results agree well with the experimental values

which indicate Gao-Yong compressible turbulence model is suitable for the prediction of shock wave turbulent boundary layer interaction in two-dimensional compression corner flows.

Abstract

including surface pressure distribution

boundary-layer static pressure profiles and mean velocity profiles.The numerical results agree well with the experimental values

which indicate Gao-Yong compressible turbulence model is suitable for the prediction of shock wave turbulent boundary layer interaction in two-dimensional compression corner flows.

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相关机构

School of Aeronautics and Astronautics,Shanghai Jiao Tong University

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics

Department of Aeronautical and Automotive Engineering, Loughborough University, Loughborough, Leicestershire, LE11 3TU, United Kingdom

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