Numerical Study of Shockwave Induced Boundary Layer Separation Control using Plasma Actuators Conference Paper uri icon


  • In this study an efficient numerical code for shockwave boundary layer interaction (SWBLI) is developed and non-thermal surface plasma actuation is evaluated for effective shockwave induced boundary layer separation control within supersonic inlets. Specifically, high speed MHD plasma actuators are of interest, in these, localized ionization is produced close to the wall surface and then accelerated using magnetic field. A time dependent computational 2D Navier-Stokes solver for shockwave boundary layer interaction is developed. To replicate the experiments done at large boundary layer thickness, the code is divided in time independent and time dependent regimes to significantly reduce computation time. Further, time and space dependent force and volumetric heating are included to account for effects of plasma actuation. Computational results are in good agreement with experiments in terms of flow structure as shown by schlieren imaging, acetone planar laser scattering and static pressure profile on the test section wall. Additionally, non-thermal plasma actuation using magnetically driven plasma column is seen to be effective in delaying incipient separation and reduce the strength of recirculation. Copyright 2008 by Authors.

name of conference

  • 46th AIAA Aerospace Sciences Meeting and Exhibit

published proceedings

  • 46th AIAA Aerospace Sciences Meeting and Exhibit

author list (cited authors)

  • Kalra, C., Shneider, M., & Miles, R.

citation count

  • 4

complete list of authors

  • Kalra, Chiranjeev||Shneider, Mikhail||Miles, Richard

publication date

  • January 2008