Model surface conductivity effect for the electromagnetic heat shield in re-entry flight

DOI10.1063/1.3054149zbMath1182.76499OpenAlexW2044660110MaRDI QIDQ5304347

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Publication date: 18 March 2010

Published in: Physics of Fluids (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1063/1.3054149

zbMATH Keywords

supersonic flowplasma diagnosticsspace vehicleselectromagnetic shieldingsurface conductivityplasma magnetohydrodynamicsplasma shock waves

Mathematics Subject Classification ID

Fluid mechanics (76-XX)

Related Items (1)

Numerical methodologies for magnetohydrodynamic flow control for hypersonic vehicles

Cites Work

• Experimental investigation of the electromagnetic effect on a shock layer around a blunt body in a weakly ionized flow
• Magnetic control of flow past a blunt body: Numerical validation and exploration
• Model and magnetic configuration effect on shock layer enhancement by an applied magnetic field

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