Prospects of MHD flow control for hypersonics

Llneberry, J. T.; Rosa, R.J.; Bityurin, V. A.; Botcharov, A. N.; Potebnya, V. G.

doi:10.2514/6.2000-3057

Cited by 22 publications

(13 citation statements)

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“…In one of the pioneering studies of supersonic MHD flow past a blunt body [3] it was shown that an increase in the MHD interaction parameter leads to an increase in the bow shock stand-off from the body surface. The modern investigations include studies [4][5][6][7][8][9][10][11][12][13][14][15][16]. In [4][5][6][7][8][9] the Hall effect was neglected.…”

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confidence: 99%

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Magnetohydrodynamic interaction in hypersonic air flow past a blunt body

Bityurin¹,

Bocharov²

2006

Fluid Dyn

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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.

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confidence: 99%

“…The modern investigations include studies [4][5][6][7][8][9][10][11][12][13][14][15][16]. In [4][5][6][7][8][9] the Hall effect was neglected. In [7] the effect of chemical nonequilibrium on the MHD interaction was considered.…”

mentioning

confidence: 99%

Magnetohydrodynamic interaction in hypersonic air flow past a blunt body

Bityurin¹,

Bocharov²

2006

Fluid Dyn

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“…The application of MHD interaction for the peak heat flux reduction on re-entry bodies proposed by A.Kantrovitz [22] has initiated wide international efforts on MHD energy conversion method undertaken during several decades of the second half of the 20 th century and resulted in several MHD technologies: pulse power MHD generators, fossil fuel fired MHD generators, nonequilibrium noble gas MHD generator. Recently, the MHD applications to the more general MHD flow/flight control [23][24] under hypersonic flight conditions and on-board electrical power generation at MWs level were reviewed [25][26][27][28]. A successful MHD application for hypersonic wind tunnel been developed in the former Soviet Union [29] on a base of seeded airflow is now considered in the USA with utilization of e-beam ionization technique [30].…”

Section: Introductionmentioning

confidence: 99%

EM advanced flow/flight control

Батенин

2001

39th Aerospace Sciences Meeting and Exhibit

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The status of research in a newly formulated area -Magneto-Plasma-Aerodynamics (MPA) for aerospace applications performed at Institute of High Temperatures of Russian Academy of Sciences is reviewed. Motivations, background, current tasks and future work plans are discussed. Promising areas for applications: total drag reduction, shock wave attenuation, plasma and MHD assisted high speed combustion, MHD flow control and on-board electrical power generation -are indicated. IntroductionDuring last decade a new approach to a control of air flow around vehicles is discussed with increasing intensity [1][2][3][4][5]. This approach is based on the controllable momentum and energy redistribution in up-coming flow by means of on-board generated external electrical and magnetic fields. The advantage of such an approach is related to the potentiality of the electromagnetic fields being able, in principle, to create a remote impact on flow parameters instead of the contact interaction of vehicle surface with airflow typically used in conventional gasdynamics. Properly distributed energy sources and sinks Q e = jE and the MHD body force F=jxB result in flow field modification and, in particular, gasdynamics parameters distribution over the vehicle surface. Pressure and skin friction on the vehicle surface define the total drag (or trust) and the total moment, whereas the temperature (enthalpy) defines the heat fluxes to the surface. Moreover, the plasma conditions in combination with external electric and magnetic fields can result in more or less significant modification of transport properties of the flowing media, such as viscosity, heat and electrical conductivity, and in change in the effective speed of sound, which is of primary importance especially for supersonic flow evolution over bodies. The heat release in up-coming flow as an effective technique to reduce the total drag and the peak heat flux of blunted bodies in supersonic flows are discussed in a number of papers [6][7][8]. It was shown that the properly localized concentrated heat release could provide a very significant total drag reduction with the rather high effectiveness when the energy consumption is much less than the drag force work decreasing. Such an energy deposition can be realized with one of the type of gas discharge already tested in laboratories: plasma jet (PJ) [9-10], the high frequency (HF) discharge of the capacitive type [11][12], the microwave discharge (MW) [13][14], the combined laser or e-beam + HF or MW discharge [15][16]. The pioneering studies of plasma aerodynamics effects were performed in 80 th in the former Soviet Union with shock tunnels [17-18] on the shock wave propagation

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“…39 A complicating factor of MHD boundary layer control is that Hall effects are likely to be present in the low-density, high-magnetic-field scenarios typical of MHD plasma boundary layer control applications. 12 The Hall effect arises in low density flows when the period of revolution of an electron about a magnetic field line becomes appreciable compared to the time between electron-neutral collisions. The magnitude of this effect is described by the ratio of these two times, or the Hall parameter,…”

Section: Poggie and Gaitondementioning

confidence: 99%

“…The inevitability of Hall effects in low-density flows has been known for some time, and numerous schemes have been developed for dealing with them. 12,39,40 It is conceivable that the Hall forces could be exploited in conjunction with the Faraday force to aid in controlling the boundary layer. For the scenario shown in Figure 3, a boundary layer crossflow would be created that might be used to negate crossflow instability on a swept wing, for example.…”

Section: Poggie and Gaitondementioning

confidence: 99%