Progress in Computational Magneto-Fluid-Dynamics for Flow Control

  • J. S. Shang
  • P. G. Huang
  • D. B. Paul
Conference paper


In the late 1990’s a promising and innovative concept of the Magnetohydrodynamic (MHD)-bypass scramjet engine rejuvenated interest in magnetoaerodynamic research worldwide [1]. Many interdisciplinary ideas were put forth in the areas of plasma actuator for flow control, MHD propulsion, remote energy deposition for drag reduction, radiation driven hypersonic wind tunnel, sonic boom meditation, and enhanced plasma ignition and combustion stability [2,3]. Extensive and in-depth research however has revealed that additional and refined fidelity of physics for modeling and analyzing are required to reach a conclusive assessment for the MHD-bypass scramjet engine [4]. From this lesson learned; most recent research activities tend to refocus on more basic and simpler aerodynamic-electromagnetic interaction phenomena.


Flow Control Dielectric Barrier Discharge Electric Field Intensity Hypersonic Flow Plasma Actuator 
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Copyright information

© Springer-Verlag Berlin Heidelberg 2009

Authors and Affiliations

  • J. S. Shang
    • 1
  • P. G. Huang
    • 1
  • D. B. Paul
    • 2
  1. 1.Wright State UniversityDaytonUSA
  2. 2.Wright-Patterson Air Force BaseUSA

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