Shockwave Induced Turbulent Boundary Layer Separation Control with Plasma Actuators Conference Paper uri icon


  • In this study we report further experiments done with surface plasma control of shock- wave boundary layer interaction (SWBLI). These experiments are designed to evaluate surface plasma actuators for effective shockwave induced boundary layer separation control within supersonic inlets. A transverse plasma column is generated close to the wall using embedded electrodes in the wall surface and accelerated by applying magnetic field perpendicular to the current and flow direction. It was reported earlier that when a weak shock generator (10) is used to generate the impinging shockwave, while no separation occurs without plasma control, a small current plasma column (< 100mA) at 1-3 Tesla is enough to induce separation by flow retardation in the interaction region. Also, in the absence of magnetic field, no change in the flow structure is seen, indicating marginal role of joule heating in the process. Further experiments were done at high currents 100- 300 mA; for flow acceleration in the interaction region. At these relatively high currents, the plasma actuation is able to delay the incipient separation. Additionally, direct flow structure visualization is done using acetone injection into the test section for planar laser scattering. 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., Zaidi, S., & Miles, R.

citation count

  • 8

complete list of authors

  • Kalra, Chiranjeev||Zaidi, Sohail||Miles, Richard

publication date

  • January 2008