| Numerical study of compression corner flowfield using Gao-Yong turbulence model |
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| 作者姓名： | GAO Ge ZHANG Chang-xian YAN Wen-hui WANG Yong |
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| 作者单位： | 1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100091, China;2. Chinese Aeronautical Establishment, Beijing 100012, China;1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100091, China;2. Chinese Aeronautical Establishment, Beijing 100012, China;1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100091, China;2. Chinese Aeronautical Establishment, Beijing 100012, China;1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100091, China;2. Chinese Aeronautical Establishment, Beijing 100012, China |
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| 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.
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| 关 键 词： | shock wave turbulent boundary layer interaction |
| 收稿时间： | 2011/8/16 0:00:00 |
| 修稿时间： | 2011/10/31 0:00:00 |
Numerical study of compression corner flowfield using Gao-Yong turbulence model |
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| GAO Ge,ZHANG Chang-xian,YAN Wen-hui,WANG Yong.Numerical study of compression corner flowfield using Gao-Yong turbulence model[J].Journal of Aerospace Power,2012,27(1):124-128. |
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| Authors: | GAO Ge ZHANG Chang-xian YAN Wen-hui and WANG Yong |
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| Institution: | 1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100091, China
2. Chinese Aeronautical Establishment, Beijing 100012, China |
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| Abstract: | 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. |
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| Keywords: | shock wave turbulent boundary layer interaction |
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