Numerical study of boundary layer separation control using magnetogasdynamic plasma actuators

Journal Article · Thu Oct 15 00:00:00 EDT 2009 · Physics of Fluids (1994)

DOI:https://doi.org/10.1063/1.3233658· OSTI ID:22038468

Kalra, Chiranjeev S; Shneider, Mikhail N; Miles, Richard B ^[1]

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1. Department of Mechanical and Aerospace Engineering, Applied Physics Group, Princeton University, Princeton, New Jersey 08544 (United States)

In this study, an efficient, time dependent, two-dimensional Navier-Stokes numerical code for shockwave boundary layer interaction in air is developed. Nonthermal surface plasma actuation is evaluated for effective shockwave induced boundary layer separation control within supersonic inlets. Specifically, high speed magnetogasdynamic plasma actuators are of interest. In these, localized ionization is produced close to the wall surface and then the flow is accelerated using strong magnetic fields. To replicate the experiments done at large boundary layer thickness, the code is divided into time independent and time dependent regimes to significantly reduce computation time. Computational results are in good agreement with experiments in terms of the flow structure as shown by Schlieren imaging, acetone planar laser scattering, and the static pressure profile on the test section wall.

• OSTI ID: 22038468
• Journal Information: Physics of Fluids (1994), Vol. 21, Issue 10; Other Information: (c) 2009 American Institute of Physics; Country of input: International Atomic Energy Agency (IAEA); ISSN 1070-6631
• Country of Publication: United States
• Language: English

Related Subjects

70 PLASMA PHYSICS AND FUSION TECHNOLOGY
ACETONE
ACTUATORS
AIR
BOUNDARY LAYERS
CALCULATION METHODS
INTERACTIONS
IONIZATION
LASER SPECTROSCOPY
MAGNETIC FIELDS
MAGNETOGASDYNAMICS
MAGNETOHYDRODYNAMICS
NAVIER-STOKES EQUATIONS
NUMERICAL ANALYSIS
PLASMA
SHOCK WAVES
SURFACES
THICKNESS
TIME DEPENDENCE
TWO-DIMENSIONAL CALCULATIONS