Flow control using various plasma and aerodynamic approaches (Short review)

Фомин, В. М.; Tretyakov, P. K.; Taran, J. P.

doi:10.1016/j.ast.2004.01.005

Cited by 139 publications

(41 citation statements)

References 10 publications

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“…Even though as early as the beginning of the 1980s anomalous behaviors of shock waves in front of bodies traveling in weakly ionized gases have been reported. 2 The possibilities of application of such a method in the aerodynamic field are very wide. These applications include viscous drag reduction, boundary layer and separation control in subsonic airflow, shock modification, drag reduction, redistribution of thermal and mechanical load on structures, mitigation of supersonic boom, and increase in aircraft maneuverability.…”

Section: Introductionmentioning

confidence: 99%

Comparison between Mach 2 rarefied airflow modification by an electrical discharge and numerical simulation of airflow modification by surface heating

et al. 2009

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This study is devoted to numerical and experimental investigations about the influence of an electrical discharge over a flat plate immersed in a rarefied Mach 2 airflow. Regarding the experimental work, a negative dc discharge is created by applying a potential difference gap between two spanwise aluminum electrodes flush mounted on the plate. The electrode placed close to the leading edge is connected to the negative dc voltage, the second one is grounded. The influence due to the presence of the electric discharge is investigated with a glass Pitot tube by measuring the pressure proles above the flat plate. These experimental results are compared to the numerical work, where the effect of a surface temperature increase is simulated. Different effects can be attributed to the electrical discharge: the ionization of the gas above the plate with the creation of charged species, the acceleration of the positive charged species, the heat of the gas volume above the flat plate, and the heating of the surface of the flat plate. The Pitot probe measurements have shown a thickening of the boundary layer and the increasing of the angle of the shock wave, and the simulation of the surface temperature increase shows the same effect. These arguments let to think that the heating effect due to the temperature increase in the flat plate is the major one among the other effects mentioned above.

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Section: Introductionmentioning

confidence: 99%

Comparison between Mach 2 rarefied airflow modification by an electrical discharge and numerical simulation of airflow modification by surface heating

et al. 2009

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“…However, a number of groups working simultaneously 10−18 led toward the gradual acceptance that the primary factor in the observed dynamics is thermal. Experimental efforts by Merriman et al 19 21 have included a review of different methods of plasma control. Despite the more balanced understanding of thermal effects within different communities, there do remain finer effects of ionization, which continue to be investigated.…”

Section: B Past Workmentioning

confidence: 99%

Computational Study of Shock Mitigation and Drag Reduction by Pulsed Energy Lines

2006

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A series of numerical experiments were performed in which energy was deposited ahead of a cone traveling at supersonic/hypersonic speeds. The angle of attack was zero, and the cone half-angles ranged from 15 to 45 deg. The Mach numbers simulated were 2, 4, 6, and 8. The energy was deposited instantaneously along a finite length of the cone axis, ahead of the cone's bow shock, causing a cylindrical shock wave to push air outward from the line of deposition. The shock wave would sweep the air out from in front of the cone, leaving behind a low-density column/tube of air, through which the cone (vehicle) propagated with significantly reduced drag. The greatest drag reduction observed was 96%. (One-hundred percent drag reduction would result in the complete elimination of drag forces on the cone.) The propulsive gain was consistently positive, meaning that the energy saved as a result of drag reduction was consistently greater than the amount of energy "invested" (i.e., deposited ahead of the vehicle). The highest ratio of energy saved/energy invested was approximately 6500% (a 65-fold "return" on the invested energy). We explored this phenomenon with a high-order-accurate multidomain weighted essentially nonoscillatory finite difference algorithm, using interpolation at subdomain boundaries. This drag-reduction/shock-mitigation technique can be applied locally or globally to reduce the overall drag on a vehicle.

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“…Annual conferences and workshops on ELFC have been organized in the United States and Russia since 1997 by the AIAA, the Joint Institute of High Temperatures in Moscow, and the Leninetz Holding Company in St. Petersburg, Russia. The proceedings of the aforementioned conferences, together with recent reviews [2][3][4][5], have illustrated the wide advantages of ELFC for aerodynamic drag reduction.…”

Section: A N Bmentioning

confidence: 99%

Interaction of Microwave-Generated Plasma with a Hemisphere Cylinder at Mach 2.1

Knight

Kolesnichenko²,

Brovkin³

et al. 2009

AIAA Journal

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Microwave energy deposition is a novel method for flow control in high-speed flows. Experiments have demonstrated its capability for beneficial flowfield modification in supersonic flow including, for example, drag reduction for blunt bodies. A fully three-dimensional, time-accurate gas dynamic code has been developed for simulating microwave energy deposition in air and the interaction of the microwave-generated plasma with the supersonic flow past a blunt body. The thermochemistry model includes 23 species and 238 reactions. The code is applied to the simulation of microwave energy deposition in supersonic flow past a hemisphere cylinder. The computed centerline surface pressure is compared with the experiment. The interaction of the microwave-generated plasma with the flowfield structure is examined. Nomenclature c p i = specific heat at constant pressure for species i D = diameter of cylinder E, E o = electric field, maximum electric field H = total enthalpy per unit mass of mixture h o f i = heat of formation of species i at temperature T ref h i = static enthalpy of species i per unit mass of species i h = static enthalpy per unit mass of mixture K k = reaction coefficient for reaction k k = Boltzmann constant, 1:38 10 23 J=K k E = microwave wave number, 2= M = representative mass for ions and neutrals M i = molecular weight of species i, kg=kg mol M i = species i (e.g., M 1 e) M 1 = Mach number m = number of reactions m e = mass of electron N = total concentration of species excluding electrons, cm 3 N e , N crit e = electron concentration, critical electron concentration, cm 3 N i = concentration of species i, cm 3 n = number of species including electrons p = static pressure _ p i k = rate of production of species i from reaction k Fig. 1 Interaction of microwave-generated plasma with cylinder. Fig. 2 Centerline pressure vs time. _ q = rate of heating of gas per unit volume R = universal gas constant, 8314 J=kg mol K T = static (translational) temperature of mixture T e = electron temperature u i = mass-averaged velocity component in i direction V dr = drift velocity x i = Cartesian coordinate Y i = mass fraction of species i, Y i i = i = fraction of h i converted into heating of gas h i = rate of change in enthalpy due to reaction i = 2m e =M " = total energy per unit mass of mixture = wavelength of microwave = rotational relaxation factor, dimensionless e = effective frequency of electron collisions 0 ik , 00 ik

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Flow control using various plasma and aerodynamic approaches (Short review)

Cited by 139 publications

References 10 publications

Comparison between Mach 2 rarefied airflow modification by an electrical discharge and numerical simulation of airflow modification by surface heating

Comparison between Mach 2 rarefied airflow modification by an electrical discharge and numerical simulation of airflow modification by surface heating

Computational Study of Shock Mitigation and Drag Reduction by Pulsed Energy Lines

Interaction of Microwave-Generated Plasma with a Hemisphere Cylinder at Mach 2.1

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