Control of High Subsonic Cavity Flow Using Plasma Actuators

Yugulis, Kevin; Gregory, James W.; Samimy, Mo

doi:10.2514/6.2013-679

Cited by 7 publications

(2 citation statements)

References 25 publications

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“…Active control methods employ external energy/ momentum sources to control the cavity flow. e common active control methods include mass injection [17][18][19][20], slot blowing [21], microjet actuators [22], steady blowing [23,24], plasma actuators [25][26][27][28][29], miniature fluidic actuators, speakers and resonant tubes [30], and oscillating ramps and fences [31]. e active control methods can offer attractive noise suppression and can adjust control parameters according to different flow conditions.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation Study on Aeroacoustic Characteristics within Deformable Cavities

Ning

Shunshan

Zhang

et al. 2019

Shock and Vibration

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Cavity flow phenomena are encountered in many kinds of aviation vehicles. The flow-induced noise can easily cause structure resonance and fatigue damages. Therefore, the study on the mechanism and effective control methods of cavity noise are very important to engineering applications. A new active control method was proposed based on the deformable cavity in order to mitigate the cavity noise. Large eddy simulation (LES) and computational aeroacoustics (CAA) are combined to simulate a typical open cavity noise. The results show the first mode sound-pressure level (SPL) of tonal noise decreases gradually while the first mode frequency sharply jumps within a small range of the slant angle of the trailing and bottom wall. In addition, with the increase in the slant angle, the decrease of the first mode SPL of tonal noise at Mach 0.6 is more significant than that at Mach 0.85, but the increase of the first mode frequency at Mach 0.85 is more dramatical than that at Mach 0.6. The proposed method can not only reduce the first mode SPL obviously but also increase the first mode frequency dramatically, which makes it different from the natural frequency of the cavity structure and sequentially helps the cavity avoid fatigue damages from resonance.

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation Study on Aeroacoustic Characteristics within Deformable Cavities

Ning

Shunshan

Zhang

et al. 2019

Shock and Vibration

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“…A lot of work focusing on plasma flow control has appeared in recent years. The plasma actuator has been used in many areas, such as separation control on airfoils, [4][5][6][7][8][9] jet mixing intensification, [10] laminar and turbulent flow transition control, [11] flow separation suppression for turbine blades, [12] dynamic stall vortex control of oscillating airfoils, [13] plasma slats and flaps for aircrafts, [14] lift enhancement on airfoils, [15] cavity tones control, [16] and boundary layer acceleration. [17] In most early studies, the waveform of the voltage supplied to the electrodes was AC sine wave, and the discharge was on a timescale of milliseconds which is called millisecond surface dielectric barrier discharge (MSDBD).…”

Section: Introductionmentioning

confidence: 99%

Wind tunnel experiments on flow separation control of an Unmanned Air Vehicle by nanosecond discharge plasma aerodynamic actuation

Chen

Liang

2016

Chinese Phys. B

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Plasma flow control (PFC) is a new kind of active flow control technology, which can improve the aerodynamic performances of aircrafts remarkably. The flow separation control of an unmanned air vehicle (UAV) by nanosecond discharge plasma aerodynamic actuation (NDPAA) is investigated experimentally in this paper. Experimental results show that the applied voltages for both the nanosecond discharge and the millisecond discharge are nearly the same, but the current for nanosecond discharge (30 A) is much bigger than that for millisecond discharge (0.1 A). The flow field induced by the NDPAA is similar to a shock wave upward, and has a maximal velocity of less than 0.5 m/s. Fast heating effect for nanosecond discharge induces shock waves in the quiescent air. The lasting time of the shock waves is about 80 μs and its spread velocity is nearly 380 m/s. By using the NDPAA, the flow separation on the suction side of the UAV can be totally suppressed and the critical stall angle of attack increases from 20° to 27° with a maximal lift coefficient increment of 11.24%. The flow separation can be suppressed when the discharge voltage is larger than the threshold value, and the optimum operation frequency for the NDPAA is the one which makes the Strouhal number equal one. The NDPAA is more effective than the millisecond discharge plasma aerodynamic actuation (MDPAA) in boundary layer flow control. The main mechanism for nanosecond discharge is shock effect. Shock effect is more effective in flow control than momentum effect in high speed flow control.

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Control of oblique shock wave/boundary layer interactions using plasma actuators

2013

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Control of High Subsonic Cavity Flow Using Plasma Actuators

Cited by 7 publications

References 25 publications

Numerical Simulation Study on Aeroacoustic Characteristics within Deformable Cavities

Numerical Simulation Study on Aeroacoustic Characteristics within Deformable Cavities

Wind tunnel experiments on flow separation control of an Unmanned Air Vehicle by nanosecond discharge plasma aerodynamic actuation

Control of oblique shock wave/boundary layer interactions using plasma actuators

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