Numerical simulation of hypersonic magnetohydrodynamic flows

Hoffmann, Klaus A.; Damevin, Henri-Marie; Dietiker, Jean-François

doi:10.2514/6.2000-2259

Cited by 47 publications

(24 citation statements)

References 22 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: 59%

“…32a) is an increasing function of the applied magnetic field, while the shock stand-off distance (Fig. 32b) is almost unchanged, as already observed by Hoffmann-Damevin-Dietiker [91]. The reason for the reduction of magnetic effectiveness on the plasma flow is ascribed to the fact that the retarding magnetic force F m is not more able to overcome the accelerating effect, which is larger due to the high Mach number value.…”

Section: Mhd Effect On a Chemical Frozen Gassupporting

confidence: 56%

See 1 more Smart Citation

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: 59%

Section: Mhd Effect On a Chemical Frozen Gassupporting

confidence: 56%

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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show abstract

“…7,8 Especially, the recent advancement of the computational fluid dynamic ͑CFD͒ technique makes it possible to numerically analyze the phenomena. 3,9,10 Among them, Matsushita 11 carried out the assessment of the electromagnetic flow control ͑i.e., head-flux reduction at the stagnation point͒ during the reentry flight from the lower earth orbit ͑LEO͒, like that of the U.S. space shuttle, and has pointed out that the electromagnetic field generated around the vehicle has sufficient influence on a flow around the vehicle and it may reduce the heat flux on the vehicle significantly. 11 For this assessment, he employed the magnetohydrodynamic ͑MHD͒ simulation of the flow.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the electromagnetic effect on a shock layer around a blunt body in a weakly ionized flow

et al. 2006

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A reentry vehicle is exposed to a partially ionized flow during the reentry flight. For such a flight, a strong magnet mounted on the vehicle, which generates the magnetic field around the vehicle, is suggested to affect a surrounding ionized flow and make it possible to control the flow. Such an electromagnetic effect on the flow is investigated experimentally by using a small arc-jet wind tunnel. In the experiment, the translational temperature distribution in the shock layer around a magnetized blunt body in a supersonic, weakly ionized, argon flow is determined by applying an absorption spectroscopic technique. For the absorption spectrum affected by the magnetic field, the temperature determination method was newly developed. The temperature distribution thus determined for the shock layer shows that the applied magnetic field significantly affects the shock layer or, specifically, the shock standoff distance and enhances it.

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“…Hoffmann et al, (2000) [1]), after the first multidimensional work by Powell (1995) [2], to calculate some test cases. Hoffmann et al, (2000) [1]), after the first multidimensional work by Powell (1995) [2], to calculate some test cases.…”

Section: Introductionmentioning

confidence: 99%

MHD of Aircraft Re-entry: Limits and Perspectives

Seller¹,

Capitelli²,

Longo³

et al. 2005

AIP Conference Proceedings

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Articles you may be interested inTrajectory optimization study of a lifting body re-entry vehicle for medium to intermediate range applications AIP Conf. Proc. 1493, 782 (2012); 10.1063/1.4765577 Model surface conductivity effect for the electromagnetic heat shield in re-entry flight Phys. Fluids 20, 127103 (2008); 10.1063/1.3054149 MHD waves in stratified and dissipative plasmas AIP Conf.Abstract: In the present work, starting from classical MHD scheme, based on Maxwell equations, Euler fluid dynamic equations and generalised Ohm law, a critical study of fluid dynamics, electromagnetism, chemical and physical behaviour of plasma is carried out, and then a aircraft re-entry MHD numerical scheme is implemented. This scheme is used for MHD calculations in different conditions, in the range of low magnetic force and intermediate electrical conductivity. Initial imposed magnetic fields are uniform, but also some cases with coil generated magnetic fields are considered. Calculations of magnetic field and induced currents are extended also inside the blunt body. Results show interesting physical and electromagnetic effects. Comparison with other methods shows possible development in keeping into account other physical and chemical effects.

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Numerical simulation of hypersonic magnetohydrodynamic flows

Cited by 47 publications

References 22 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

Experimental investigation of the electromagnetic effect on a shock layer around a blunt body in a weakly ionized flow

MHD of Aircraft Re-entry: Limits and Perspectives

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