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A numerical study of shock wave/boundary layer interaction in a supersonic compressor cascade

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Abstract

A numerical analysis of shock wave/boundary layer interaction in transonic/supersonic axial flow compressor cascade has been performed by using a characteristic upwind Navier-Stokes method with various turbulence models. Two equation turbulence models were applied to transonic/supersonic flows over a NACA 0012 airfoil. The results are superion to those from an algebraic turbulence model. High order TVD schemes predicted shock wave/boundary layer interactions reasonably well. However, the prediction of SWBLI depends more on turbulence models than high order schemes. In a supersonic axial flow cascade at M=1.59 and exit/inlet static pressure ratio of 2.21, k-μ and Shear Stress Transport (SST) models were numerically stables. However, the k-μ model predicted thicker shock waves in the flow passage. Losses due to shock/shock and shock/boundary layer interactions in transonic/supersonic compressor flowfields can be higher losses than viscous losses due to flow separation and viscous dissipation.

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Authors and Affiliations

  1. School of Mechanical Engineering, Yeungnam University, Gyongsan, 712-160, Korea

    Dong Joo Song (Professor)

  2. Graduate Student, Graduate School of Mechanical Engineering, Yeungnam University, Gyongsan, Korea

    Hyun Chul Hwang & Young In Kim

Authors
  1. Dong Joo Song
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  2. Hyun Chul Hwang
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  3. Young In Kim
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Correspondence to Dong Joo Song.

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Song, D.J., Hwang, H.C. & Kim, Y.I. A numerical study of shock wave/boundary layer interaction in a supersonic compressor cascade. KSME International Journal 15, 366–373 (2001). https://doi.org/10.1007/BF03185220

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  • DOI: https://doi.org/10.1007/BF03185220

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