Effect of Plasma Actuator Placement on the Airfoil Efficiency at Poststall Angles of Attack

Salmasi, A.; Shadaram, Abdollah; Taleghani, Arash Shams

doi:10.1109/tps.2013.2280612

Cited by 23 publications

(14 citation statements)

References 15 publications

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“…Kumar et al [20] also investigated the control of drag force on a square cylinder using two detached splitter plates at Re = 150-200. In addition to these studies, other studies have also used new active methods such as a modulated pulse jet (MPJ) [21][22][23] or plasma operators [24][25][26][27][28] From the above mentioned discussion and to the best of our knowledge, it can be concluded that fluid flow and wake behavior of a square cylinder with an attached splitter at the rear side have been less investigated and analyzed in the available literature. In particular, there is no corresponding work employing the lattice Boltzmann method (LBM) in the case of such geometry.…”

Section: Introductionmentioning

confidence: 99%

Passive control of wake flow behind a square cylinder using a flat plate

et al. 2023

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In this study, control over the wake flow of a single square cylinder exercised by a flat plate attached to the rear side of the cylinder is analyzed numerically via the lattice Boltzmann method. The Reynolds number (Re) is fixed at 150, and the length of the plate is varied from 0.1 to 8.5. Three distinct flow modes are observed in this study: unsteady, transient, and steady flow in the cases of plate lengths (L) in the ranges 0.1 ≤L≤ 6.5, 6.75 ≤L≤ 7.5, and 7.75 ≤L≤ 8.5, respectively. The streamlines exhibit different flow structures, termed hairpin-like, ellipse-like, and elongated bubble-like, at different values of L. Complete wake control is achieved at plate lengths beyond 7.75. This study reveals that the drag and lift coefficients exhibit unsteadiness at short plate lengths in early time steps, but as the plate length increases, unsteadiness slows down and eventually disappears, confirming the steady flow pattern. The mean drag coefficient (CDm), Strouhal number (St), and root-mean-square value of drag and lift coefficients (CDrms; CLrms) are reduced by maximums of 23.5%, 100%, 84.6%, and 99.5%, respectively, as a result of the presence of the plate.

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Section: Introductionmentioning

confidence: 99%

Passive control of wake flow behind a square cylinder using a flat plate

et al. 2023

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“…Torrez et al developed a control‐oriented scramjet engine model that was exercised to predict the sensitivity of the thrust with variations in the Mach number and angle of attack . Salmasi et al studied the influence of the existence of a plasma actuator on the passing flow at poststall AOA through numerical simulation and experiments . Huang et al investigated the Sabot asymmetric discard after the projectile being launched from the muzzle at various AOA .…”

Section: Introductionmentioning

confidence: 99%

Impact of angle of attack on plasma flow and electromagnetic wave propagation around hypersonic vehicles

Ouyang

Liu

Zhang

2020

Micro & Optical Tech Letters

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The flow field around the RAMC-II vehicle at differenrt angles of attack (AOA) was numerically solved using a computational fluid dynamics technique with a threedimensional model. Electron density, pressure, temperature, and collision frequency, which is given great importance in this paper. The maximal electron density, total pressure, and temperature at the same position decreases with the angle of attack on the leeward side and increases with the angle of attack on the windward side. The collision frequency is almost unaffected by AOA on the leeward side, but increases significantly with AOA on the windward side. Based on the realistic plasma sheaths obtained by hypersonic fluid model, a multilayer transmission model was used to study the electromagnetic (EM) wave propagation in plasma sheath at different AOA. The attenuation value of EM wave on the leeward (windward) side decreases (increases) with the AOA. So the influence of the AOA on the EM wave transmission must be considered in the communication of vehicle reentry. In addition, the EM wave attenuation on the leeward at the same angle of attack is always smaller than the windward side, especially at a large AOA. Therefore, the leeward side can be considered as one end of the communication to improve the communication quality. The conclusions of this paper have both theoretical and practical significance to better understand the communication"blackout" problem for the reentry of hypersonic vehicles. K E Y W O R D S angle of attack, electromagnetic wave attenuation, electron density, flow field, plasma sheath 1 | INTRODUCTIONDuring the hypersonic reentry stage of the RAMC-II mission, the surface temperature of the vehicle rises sharply due to the formation of shock waves in front of the vehicle. High temperatures cause more intense chemical reactions, such as ionization and the dissociation of gases, and results in a weakly ionized plasma layer that forms around the vehicle, such plasma layer is the so-called "plasma sheath". 1 The plasma sheath that covers hypersonic vehicles causes the communication "blackout". To avoid this communication "blackout", many studies have been conducted, such as simulation of plasma flow, 2 techniques to reduce the electron plasma density, 3-5 and the mechanism of utilizing the propagation of electromagnetic waves. [6][7][8] In the actual reentry process, the vehicle has a certain angle of attack. The influence of different angles of attack (AOA) on the flow field around hypersonic vehicles has attracted significant attention. Lin et al studied the structure of the near wake flow of a hypersonic reentry vehicle and the resulting base pressure and heat transfer. 9 Torrez et al developed a control-oriented scramjet engine model that was exercised to predict the sensitivity of the thrust with variations in the Mach number and angle of attack. 10 Salmasi et al studied the influence of the existence of a plasma actuator on the passing flow at poststall AOA through numerical simulation and experiments. 11 Huang et al investigated ...

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“…The findings are thought to make some contributions to modeling the generated ionic wind in the plasma actuators under unsteady excitation condition. This type of actuator has been used by the authors elsewhere as a means of controlling the flow on the suction side of NLF0414 and NACA4412 airfoils for lift increment and noise reduction [17][18][19].…”

Section: Introductionmentioning

confidence: 99%

Parametric study of a plasma actuator at unsteady actuation by measurements of the induced flow velocity for flow control

Taleghani

Shadaram

Mirzaei

et al. 2018

J Braz. Soc. Mech. Sci. Eng.

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The dielectric barrier discharge (DBD) plasma actuator has in the last decade emerged as an active flow control device. This paper investigates the experimental measurements concerning the instantaneous ionic wind velocity induced by DBD plasma actuator in quiescent air at atmospheric pressure. A parametric study has also been undertaken to find a realistic means of increasing the velocity of the ionic wind. The electrical and mechanical characteristics of the plasma actuator have been studied under different conditions. The aim of this article is to find ways of optimizing the geometrical and electrical parameters to obtain more effective ionic wind for flow control. The results show that increments in the excitation frequency, leads to maximum velocity at the nearer position of the surface. Further analysis show that the frequency of the vortices produced by the related actuators is exactly the same as the excitation frequency of the applied voltage. It was also found that an increase in the duty cycle correspondingly increases the power of the produced vortex shedding.

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Effect of Plasma Actuator Placement on the Airfoil Efficiency at Poststall Angles of Attack

Cited by 23 publications

References 15 publications

Passive control of wake flow behind a square cylinder using a flat plate

Passive control of wake flow behind a square cylinder using a flat plate

Impact of angle of attack on plasma flow and electromagnetic wave propagation around hypersonic vehicles

Parametric study of a plasma actuator at unsteady actuation by measurements of the induced flow velocity for flow control

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