Volume 27 Issue 1
Jan.  2012
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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.
Citation: 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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Numerical study of compression corner flowfield using Gao-Yong turbulence model

  • 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

  • Received Date: 2011-08-16
  • Rev Recd Date: 2011-10-31
  • Publish Date: 2012-01-28
    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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