Magnetohydrodynamic interaction in hypersonic air flow past a blunt body

Bityurin, V. A.; Bocharov, A. N.

doi:10.1007/s10697-006-0100-5

Cited by 41 publications

(20 citation statements)

References 15 publications

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“…31b) fields at Mach number M∞ = 3.05 using an electrical conductivity σ = 4.9x10 5 (Ωm) -1 . Results reveal that the magnetic field effectively pushes the bow shock wave further away from the blunt-body as already observed by different authors [91,92,95]. For this case, the shock envelope in the plasma field exhibits an outward displacement compared to the gas dynamic shock by a factor 2 in stand-off distance Δ (see Fig.…”

Section: Mhd Effect On a Chemical Frozen Gassupporting

confidence: 76%

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Суржиков¹,

Reynier²,

Seller³

et al. 2014

TOPPJ

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Modern problems of radiative aerothermodynamics of entering space vehicles are demonstrated and analyzed in the paper. New radiative gas dynamic problems concerned to coupling processes of non-equilibrium dissociation with radiation heat transfer in shock layers generated above large scale re-entry space vehicles returning from orbital and super orbital space mission are considered in the first part.Three-dimensional numerical simulation data on radiative aerothermodynamics of Martian entry probes Pathfinder, Exomars and Mars Science Laboratory (MSL) are presented and analyzed in the second part. It is shown that integral radiative heating of leeward surface of the entry probes exceeds corresponding convective heating.The third part is dedicated to consideration preliminary numerical simulation results on radiative gas dynamics of Galileo probes. At first, a review of the available results obtained during the mission preparation and post-flight analyses has been undertaken to select a computational matrix. This matrix has been selected by accounting for previous numerical efforts from the literature to crosscheck the results. Then, a model based on previous efforts has been set up for computing the flow-field around the probe at high altitude. Finally the test case matrix has been computed and crosschecked with existing numerical predictions performed.Some possibilities of innovative magneto-hydrodynamic (MHD) technologies being applied to solve problems of re-entry vehicles heat protection are discussed in the fourth part.All presented data demonstrate necessity of further development of the radiative aerothermodynamics based on state-tostate approaches.

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Section: Mhd Effect On a Chemical Frozen Gassupporting

confidence: 76%

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Суржиков¹,

Reynier²,

Seller³

et al. 2014

TOPPJ

View full text Add to dashboard Cite

show abstract

Section: Mhd Effect On a Chemical Frozen Gassupporting

confidence: 76%

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Суржиков¹,

Reynier²,

Seller³

et al. 2014

TOPPJ

View full text Add to dashboard Cite

Modern problems of radiative aerothermodynamics of entering space vehicles are demonstrated and analyzed in the paper. New radiative gas dynamic problems concerned to coupling processes of non-equilibrium dissociation with radiation heat transfer in shock layers generated above large scale re-entry space vehicles returning from orbital and super orbital space mission are considered in the first part. Three-dimensional numerical simulation data on radiative aerothermodynamics of Martian entry probes Pathfinder, Exomars and Mars Science Laboratory (MSL) are presented and analyzed in the second part. It is shown that integral radiative heating of leeward surface of the entry probes exceeds corresponding convective heating. The third part is dedicated to consideration preliminary numerical simulation results on radiative gas dynamics of Galileo probes. At first, a review of the available results obtained during the mission preparation and post-flight analyses has been undertaken to select a computational matrix. This matrix has been selected by accounting for previous numerical efforts from the literature to crosscheck the results. Then, a model based on previous efforts has been set up for computing the flow-field around the probe at high altitude. Finally the test case matrix has been computed and crosschecked with existing numerical predictions performed. Some possibilities of innovative magneto-hydrodynamic (MHD) technologies being applied to solve problems of re-entry vehicles heat protection are discussed in the fourth part. All presented data demonstrate necessity of further development of the radiative aerothermodynamics based on state-tostate approaches.

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“…The Hall effect, which we have neglected here within the shock, should also be taken into account in a further work, since it can be shown that the Hall parameters β e (for electrons) and β i (for ions) increase with altitude. The Hall effect is most developed at 60−70 km height and is therefore most studied in that region (Bityurin & Bocharov 2006). (ii) The first-order rotational solution we used shows how the aftershock flow is impacted by our jump relations.…”

Section: Prospectsmentioning

confidence: 99%

Analytic model of a resistive magnetohydrodynamic shock without Hall effect

Berton

2018

J. Fluid Mech.

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An analytic model of a stationary hypersonic magnetohydrodynamic (MHD) shock with an externally applied magnetic field is proposed. Basically, original jump conditions at a plane oblique shock, analogous to the Rankine–Hugoniot formulae, with a moderately resistive air plasma downstream are derived. Viscous, thermal and Hall effects are neglected, but the plasma dissociation behind the shock causing a jump of isentropic exponent is also a major input of the model. Then, a shock-fitting procedure with ambient atmospheric conditions is worked out by the coupling of these MHD jumps with thermodynamic correlations and an electric conductivity model. For an application to atmospheric entry problems, the flow behind an axisymmetric blunt-body shock is modelled with a stream function satisfying these MHD jump conditions as boundary conditions. An important feature put into evidence is a similarity rule involving the hypersonic parameter$M_{1}\cos \unicode[STIX]{x1D712}_{1}$, which shows an aerodynamic correspondence between the upstream Mach number$M_{1}$and the velocity angle$\unicode[STIX]{x1D712}_{1}$. It also emerges that curvature effects become important past$30^{\circ }$and the assumption of a spherical shock also becomes untenable past$50^{\circ }$; therefore, we limit the model of shock thickness used in the MHD fitting to$\unicode[STIX]{x1D712}_{1}<50^{\circ }$.

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Magnetohydrodynamic interaction in hypersonic air flow past a blunt body

Cited by 41 publications

References 15 publications

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Analytic model of a resistive magnetohydrodynamic shock without Hall effect

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