Numerical investigation of real gas effects on magnetohydrodynamic hypersonic flows

Anurag Gupta; Ramesh K. Agarwal

doi:10.2514/6.2001-199

Numerical investigation of real gas effects on magnetohydrodynamic hypersonic flows

Anurag Gupta, Ramesh K. Agarwal

Research output: Contribution to conference › Paper › peer-review

1 Scopus citations

Abstract

Recent research on the use of electromagnetic fields for flow control in slightly ionized plasmas has focused on improving the performance of high-speed propulsion systems by reducing drag in scramjet inlets and increasing their efficiencies. To study and establish the viability of these MHD flow control techniques, the physical modeling capability of a viscous, compressible MHD code has been extended to account for real gas effects and variable electrical conductivity. 2-D MHD solutions for nominal scramjet flowpath geometries are obtained by solving the compressible viscous MHD equations in generalized coordinates using a modified Runge-Kutta time integration scheme, second-order accurate spatial discretization and a symmetric Davis-Yee TVD flux limiter. The effect of magnetic field on scramjet inlet flowfields, with air assumed to be frozen and in thermochemical equilibrium is quantified.

Original language	English
DOIs	https://doi.org/10.2514/6.2001-199
State	Published - 2001
Event	39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States Duration: Jan 8 2001 → Jan 11 2001

Conference

Conference	39th Aerospace Sciences Meeting and Exhibit 2001
Country/Territory	United States
City	Reno, NV
Period	01/8/01 → 01/11/01

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10.2514/6.2001-199

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abstract = "Recent research on the use of electromagnetic fields for flow control in slightly ionized plasmas has focused on improving the performance of high-speed propulsion systems by reducing drag in scramjet inlets and increasing their efficiencies. To study and establish the viability of these MHD flow control techniques, the physical modeling capability of a viscous, compressible MHD code has been extended to account for real gas effects and variable electrical conductivity. 2-D MHD solutions for nominal scramjet flowpath geometries are obtained by solving the compressible viscous MHD equations in generalized coordinates using a modified Runge-Kutta time integration scheme, second-order accurate spatial discretization and a symmetric Davis-Yee TVD flux limiter. The effect of magnetic field on scramjet inlet flowfields, with air assumed to be frozen and in thermochemical equilibrium is quantified.",

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AB - Recent research on the use of electromagnetic fields for flow control in slightly ionized plasmas has focused on improving the performance of high-speed propulsion systems by reducing drag in scramjet inlets and increasing their efficiencies. To study and establish the viability of these MHD flow control techniques, the physical modeling capability of a viscous, compressible MHD code has been extended to account for real gas effects and variable electrical conductivity. 2-D MHD solutions for nominal scramjet flowpath geometries are obtained by solving the compressible viscous MHD equations in generalized coordinates using a modified Runge-Kutta time integration scheme, second-order accurate spatial discretization and a symmetric Davis-Yee TVD flux limiter. The effect of magnetic field on scramjet inlet flowfields, with air assumed to be frozen and in thermochemical equilibrium is quantified.

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ER -

Numerical investigation of real gas effects on magnetohydrodynamic hypersonic flows

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