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Plasma control of vortex flow on a delta wing at high angles of attack

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Abstract

The flow over a delta wing at high angles of attack is characterized by the presence of two large-scale primary vortices on the leeward side of the wing. These vortices contribute substantially to lift production at high angles of attack. Therefore, vortex breakdown, which can be induced by unfavorable pressure gradients or free-stream disturbances, can lead to an abrupt decrease in lift and to the emergence of a roll moment. Thus, the possibility of vortex flow control can be very useful. The problem of vortex flow control is investigated experimentally under subsonic flow parameters in the range of wing chord-based Reynolds number (0.14, 0.25) × 106. A dielectric barrier discharge (DBD) is used as an active control actuator. The data obtained by means of oil flow and smoke flow visualization, surface pressure measurements, and using a particle image velocimetry technique show that the DBD can provoke early vortex bursting. Under certain conditions (discharge excitation mode and frequency), flow excitation by the discharge actuator is found to result in vortex stabilization.

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Notes

  1. http://www.polis-instruments.ru.

Abbreviations

A 1 :

Primary vortex attachment line

A 2 :

Secondary vortex attachment line

C p :

Pressure coefficient, (p − p 0)/q ∞  + 1

c :

Wing root chord length (mm)

f :

Discharge frequency in continuous mode (kHz)

F :

Pulse packet repetition frequency in burst mode (Hz)

F + :

Reduced frequency, F c/U ∞

p :

Static pressure on the model surface (Pa)

p 0 :

Total pressure (Pa)

S 2 :

Secondary vortex separation line

t :

Time (s)

q ∞ :

Mean free-stream dynamic pressure (Pa)

U ∞ :

Mean free-stream velocity (m/s)

W :

Discharge power (Watt)

x :

Vortex breakdown position along the wing chord (mm)

y :

Vertical direction perpendicularly xz-plane (mm)

z :

Transversal direction along the wing span (mm)

α :

Angle of attack (°)

ω :

Flow vorticity in xy-plane (1/s)

χ:

Leading edge sweep angle (°)

∞:

Free-stream condition

0:

At zero local mean velocity

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Authors and Affiliations

  1. Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch of Russian Academy of Sciences (ITAM SB RAS), Institutskaya str. 4/1, Novosibirsk, 630090, Russia

    Andrey A. Sidorenko, Alexey D. Budovskiy, Anatoly A. Maslov, Boris V. Postnikov, Boris Yu. Zanin, Ilya D. Zverkov & Victor V. Kozlov

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  1. Andrey A. Sidorenko
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  2. Alexey D. Budovskiy
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  3. Anatoly A. Maslov
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  4. Boris V. Postnikov
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  5. Boris Yu. Zanin
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  6. Ilya D. Zverkov
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  7. Victor V. Kozlov
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Correspondence to Andrey A. Sidorenko.

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Sidorenko, A.A., Budovskiy, A.D., Maslov, A.A. et al. Plasma control of vortex flow on a delta wing at high angles of attack. Exp Fluids 54, 1585 (2013). https://doi.org/10.1007/s00348-013-1585-4

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  • DOI: https://doi.org/10.1007/s00348-013-1585-4

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