Direct Simulation Monte Carlo Method Applied to the Ionic Wind in Supersonic Rarefied Conditions

Menier, Eric; Lengrand, J. C.; Depussay, E.; Lago, Viviana; Leger, Lue

doi:10.2514/6.2006-3343

Cited by 4 publications

(2 citation statements)

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“…The validity of measuring the pressure by a such Pitot probe has been checked in previous studies of our group. 14,15 The displacement of the Pitot probe was ensured with a 3-axis traversing system (step resolution on each axis of 0.1 mm ± 0.02 mm on each position).…”

Section: Pressure Measurementsmentioning

confidence: 99%

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Effect of surface heating on shock wave modification by a plasma actuator in a rarefied supersonic flow over a flat plate

Coumar¹,

Joussot²,

Parisse³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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This paper describes experimental and numerical investigations focused on the shock wave modification induced by a plasma actuator. The studied model is a flat plate placed in a rarefied Mach 2 air flow. The plasma actuator is composed of two metallic electrodes set on the upper surface of the model. A negative dc potential is applied to the upstream electrode in order to generate an abnormal glow discharge and, thus, to create a weakly ionized plasma around the model. ICCD images of the flow allow the shock wave to be detected and its angle to be estimated. When the discharge is ignited, the shock wave angle increases with the discharge current. In addition, an IR camera is used to measure the increase in the surface temperature. The longitudinal distributions of the surface temperature are used as boundary conditions in the numerical simulations of the surface heating induced by the plasma actuator. This type of thermal effect is reproduced experimentally with a heating element designed to this purpose. For the same surface heating, experimental results show that the shock wave angle is higher in the case of the plasma actuator: surface heating is responsible for roughly 50% of the shock wave angle modification. The numerical simulations are used to studied the aerodynamic forces modifications in the case of the surface heating. The results are extrapolated to the plasma actuator in order to estimate the variations in the drag and lift coefficients.

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Section: Pressure Measurementsmentioning

confidence: 99%

“…15 show the evolution of F D and F L according to T w,max for the different domains of the model. Aerodynamic forces according to Tw,max for the different parts of the flat plate: a) lift force F L i of zone i, and b) drag force F D i of zone i.…”

mentioning

confidence: 99%

Effect of surface heating on shock wave modification by a plasma actuator in a rarefied supersonic flow over a flat plate

Coumar¹,

Joussot²,

Parisse³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

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Quantification of the effect of surface heating on shock wave modification by a plasma actuator in a low-density supersonic flow over a flat plate

Joussot¹,

Lago²,

Parisse

2015

Exp Fluids

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International audienceThis paper describes experimental and numerical investigations focused on the shock wave modification induced by a dc glow discharge. The model is a flat plate in a Mach 2 air flow, equipped with a plasma actuator composed of two electrodes. A weakly ionized plasma was created above the plate by generating a glow discharge with a negative dc potential applied to the upstream electrode. The natural flow exhibited a shock wave with a hyperbolic shape. Pitot measurements and ICCD images of the modified flow revealed that when the discharge was ignited, the shock wave angle increased with the discharge current. The spatial distribution of the surface temperature was measured with an IR camera. The surface temperature increased with the current and decreased along the model. The temperature distribution was reproduced experimentally by placing a heating element instead of the active electrode, and numerically by modifying the boundary condition at the model surface. For the same surface temperature, experimental investigations showed that the shock wave angle was lower with the heating element than for the case with the discharge switched on. The results show that surface heating is responsible for roughly 50 % of the shock wave angle increase, meaning that purely plasma effects must also be considered to fully explain the flow modifications observed

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Influence of Mach number and static pressure on plasma flow control of supersonic and rarefied flows around a sharp flat plate

Coumar

Lago

2017

Exp Fluids

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Direct Simulation Monte Carlo Method Applied to the Ionic Wind in Supersonic Rarefied Conditions

Cited by 4 publications

References 0 publications

Effect of surface heating on shock wave modification by a plasma actuator in a rarefied supersonic flow over a flat plate

Effect of surface heating on shock wave modification by a plasma actuator in a rarefied supersonic flow over a flat plate

Quantification of the effect of surface heating on shock wave modification by a plasma actuator in a low-density supersonic flow over a flat plate

Influence of Mach number and static pressure on plasma flow control of supersonic and rarefied flows around a sharp flat plate

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