Hypersonic Flow Past the Spherical Nose of a Body in the Presence of a Magnetic Field

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Hypersonic MHD air flow past a blunt body in the presence of an external magnetic field is considered. The MHD effect on the flow consists in a significant increase in the shock wave stand-off from the body surface and a significant reduction in the heat flux to the wall (up to 50%). It is shown that even in the presence of a strong Hall effect the intensity of the magnetohydrodynamic interaction in the plasma behind the shock wave remains at a high level commensurable with the ideal case of the absence of a Hall effect.

mentioning

confidence: 99%

“…In [10][11][12] the inlet to a scramjet was analyzed in the 2D formulation. In [13] the MHD effects in the nose of a body were considered with allowance for the Hall effect.…”

mentioning

confidence: 99%

Magnetohydrodynamic interaction in hypersonic air flow past a blunt body

Bityurin¹,

Bocharov²

2006

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“…However, with the increased flight velocity and altitude of modern vehicles the bow shock is more intense and equilibrium ionization in the shock-compressed plasma may be sufficient to ensure the necessary electrical conductivity (∼ 100 Cm/m). In this connection, in recent years a series of publications has appeared (see, for example, [5][6][7][8]) in which the possibility of MHD flow control is considered under the assumption, natural for these electrical conductivities, of the smallness of the induced magnetic fields (Re m 1).…”

mentioning

confidence: 99%

“…In particular, in [8] hypersonic MHD flow past a spherical nose with a magnetic dipole was investigated. The simulation was bases on the complete Navier-Stokes equations and Ohm's law with allowance for the Hall effect.…”

mentioning

confidence: 99%

Hypersonic flow past a plane magnetic dipole with parallel orientation of the magnetic moment and free-stream velocity vectors for moderate magnetic Reynolds numbers

Gubanov¹,

Лихачев²,

Medin³

2006

The two-dimensional problem of hypersonic flow past a cylindrical body with a plane magnetic dipole in the presence of an external magnetic field is considered. The magnetic moment of the dipole is parallel to the free-stream velocity. The flow parameters correspond to a velocity of 7000 m/s at an altitude of approximately 65 km in the Earth's atmosphere. The system of MHD equations (the Euler equations with volume MHD momentum and energy sources and the magnetic induction equation) was solved using the stabilization method. The calculations were carried out for two magnetic Reynolds numbers: (Re m ) 1 = 0.18 (corresponds to the parameters of the equilibrium ionized plasma in the shock layer) and (Re m ) 2 = 1.8 (the plasma conductivity increases by a factor of 10). The solutions obtained are analyzed, the effect of Re m on the flow characteristics, namely, the shock wave stand-off from the body, the configuration of the vortex structures, and the aerodynamic and ponderomotive components of the body drag, is determined.The maximum current densities are observed in the peripheral shock layer regions adjacent to the upper (with respect to the flow) corners E and F of the body, where the y-component of the magnetic field is large.

“…In the last decade interest in using the magnetohydrodynamic (MHD) method of controlling internal and external super-and hypersonic gasdynamic flows [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15] has again increased in connection with the development of hypersonic technologies. Investigations of internal flows show that supersonic channel flows can be intensively decelerated using a magnetic field and, as a result, the static pressure can be significantly increased [6][7][8][9][10].…”

mentioning

confidence: 99%

Magnetohydrodynamic control of supersonic flow past bodies: Possibilities and undesirable effects

Vatazhin¹,

Danilov²,

Гуськов³

et al. 2006

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Basic problems of super-and hypersonic magnetohydrodynamics (MHD) associated with the determination of the integral characteristics of bodies and vehicles inside which there are systems generating a uniform magnetic field are considered. Three classes of flows, namely, flow in a hypersonic multimode fixed-geometry air-intake; internal and external flow in a model of a hypersonic vehicle containing an air-intake with an MHD generator, a combustion chamber, and a supersonic nozzle; and hypersonic flow past a blunt cone are studied using numerical simulation and theoretical analysis (on the basis of the complete averaged system of Navier-Stokes equations and the electrodynamic equations). Attention is concentrated on the presence of an additional magnetic force acting on the system generating the magnetic field and, consequently, on the body and initiating an additional drag (in the case of a vehicle -reducing its thrust). Attractive possibilities for MHD flow control, namely, an increase in the degree of flow compression in the air-intake, a reduction in the ignition length in the combustion chamber, and a decrease in the heat flux to the nose of the body, are noted, as well as negative effects associated with the action of the magnetic force on the bodies considered.