Commun. Comput. Phys.,
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Volume 4.

Electrostatic-Aerodynamic Compression in Hypersonic Cylindrical Inlet

J. S. Shang 1*

1 Department of Mechanics and Materials Engineering, Wright State University, Dayton, OH 45435, USA.

Received 20 June 2007; Accepted (in revised version) 18 October 2007
Available online 28 May 2008


Hypersonic magneto-fluid-dynamic interaction has been successfully performed as a virtual leading-edge strake and a virtual cowl of a rectangular inlet. In a side-by-side experimental and computational study, the magnitude of the induced compression was found to depend on configuration and electrode placement. To better understand the interacting phenomenon the present investigation is focused on a direct current discharge at the leading edge of a cylindrical inlet for which validating experimental data is available. The present computational result is obtained by solving the magneto-fluid-dynamics equations at the low magnetic Reynolds number limit and using a nonequilibrium weakly ionized gas model based on the drift-diffusion theory. The numerical simulation provides a detailed description of the intriguing physics. After validation with experimental measurements, the computed results further quantify the effectiveness of a magneto-fluid-dynamic compression for a hypersonic cylindrical inlet. A minuscule power input to a direct current surface discharge of 8.14 watts per square centimeter of electrode area produces an additional compression of 6.7 percent for a constant cross-section cylindrical inlet.

AMS subject classifications: 65Z05, 76K05, 76W05

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Key words: Magnetohydrodynamics, hypersonic flows.

*Corresponding author.
Email: (J. S. Shang)

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