Journal of Mechanical Science and Technology

The Korean Society of Mechanical Engineers (대한기계학회)
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A Numerical Study of Shock Wave/Boundary Layer Interaction in a Supersonic Compressor Cascade

  • Song, Dong-Joo (Professor, School of Mechanical Engineering, Yeungnam University) ;
  • Hwang, Hyun-Chul (Graduate Student, Graduate School of Mechanical Engineering, Yeungnam University) ;
  • Kim, Young-In (Graduate Student, Graduate School of Mechanical Engineering, Yeungnam University)
  • Published : 2001.03.01
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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 characteristics 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-$\omega$ and Shear Stress Transport (SST) models were numerically stables. However, the k-$\omega$ 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.

Keywords

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