Flow Control over a Conical Forebody Using Duty-Cycled Plasma Actuators

Liu, Feng; Luo, Shijun; Gao, Chao; Meng, Xuanshi; Hao, Jiangnan; Wang, Jianlei; Zhao, Zijie

doi:10.2514/1.39435

Cited by 81 publications

(44 citation statements)

References 20 publications

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“…In recent years, the flow control in the burst operation mode of the plasma actuator has received much attention for its effectiveness [7][8][9][10] . This burst mode periodically generates a large vortex whose size is larger than the boundary layer.…”

Section: Control In Burst Operation Modementioning

confidence: 99%

“…The other advantages are that this is an electronic device without any moving parts, has fast response, and is thin and light in weight. There exist some studies where a plasma actuator acts as a control device for the asymmetric vortices over a slender body 9,10) . The plasma actuator was installed on the nose tip of the slender body and only a bang-bang control of the side force was accomplished (In general, it is known that a control effect at the nose tip is too sensitive for the asymmetric vortex structure to proportionally control the side force 2) ).…”

Section: Introductionmentioning

confidence: 99%

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Preliminary Experimental Study on Aerodynamic Characteristics Control of Slender Body Using DBD Plasma Actuator

Nishida

Mizuki

Miyazaki

et al. 2012

AEROSPACE TECHNOLOGY JAPAN

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Asymmetric separation vortices over a slender body at a high angle of attack exert a strong side force on the body and lead to the loss of attitude stability. We investigated the active control of the separation flow over a slender body and addressed the proportional control of the side force and the pitching moment. A flow control experiment was conducted in a wind tunnel using a cone-cylinder test body and a Dielectric Barrier Discharge (DBD) plasma actuator as a flow control device. The free-stream velocity was 9 m/s and the Reynolds number was approximately 42000. The side force coefficient was proportionally controlled within approximately ±1.0 using the actuator at the aft body, and the static stability angle of attack was controlled from 25 to 40 degrees and 65 to 85 degrees by controlling the pitching moment when the center of gravity was at the 55% position from the body apex. We estimated that a higher actuator output power is required for the effective control of the aerodynamics in a real flight. In addition, we confirmed that the actuator burst operation mode could reduce the required output power.

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Section: Control In Burst Operation Modementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Preliminary Experimental Study on Aerodynamic Characteristics Control of Slender Body Using DBD Plasma Actuator

Nishida

Mizuki

Miyazaki

et al. 2012

AEROSPACE TECHNOLOGY JAPAN

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show abstract

“…It has been found experimentally that unsteady dynamic control techniques are needed to achieve this goal. [1][2][3] Recently, Liu et al 4 reported wind-tunnel experiments that demonstrate nearly linear proportional control of lateral forces and moments over a slender conical forebody at high angles of attack by employing a novel design and placement of a pair of single dielectric barrier discharge (SDBD) plasma actuators near the cone apex combined with a duty cycle technique.…”

Section: Introductionmentioning

confidence: 99%

“…It is well known that the sign changes of side force are caused by the occurrences of additional vortex separated alternately from the port and starboard side of the body to the initial vortex pair originated from the body apex. [5][6][7] How the plasma actuations affect the asymmetric forces and vortex flow on the circular-cone forebody 4 at high angles of attack upto 70…”

Section: Introductionmentioning

confidence: 99%

Influence of Plasma Actuations on Forebody Side Forces and Wakes

Zhao

Gao

Liu

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The variation of the asymmetric force and vortex wake on a 20• circular-cone forebody with angle of attack from 35• to 70• at zero sideslip are investigated. A pair of plasma actuators is designed and placed near the apex of the forebody. The pressure distributions over the forebody are measured in a low-turbulence 3.0 m × 1.6 m low-speed open-circuit wind tunnel at freestream velocity 5 m/s and Reynolds number of 50, 000 based on the cone base diameter. The pressure data are used to calculate the side force distribution along the forebody axis and to infer the salient features of the separated flow over the forebody under three modes of controls: plasma-off, plasma port-on and plasma starboard-on. Effects of the plasma actuations on vortex wake and side force over the cone forebody at angle of attack upto 70• are identified.

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“…The sensitivity of vortex flows over slender bodies to nose-tip imperfections has been exploited for vortex control. [8][9][10] The asymmetric vortex system over slender bodies will become unsteady at sufficiently high AOAs (typically more than 65 • ). It can been anticipated that the flow pattern over after-bodies downstream will transition to Kármán vortex shedding if the cylindrical after-body is sufficiently long.…”

mentioning

confidence: 99%

Low-frequency vortex oscillation around slender bodies at high angles-of-attack

Liu

2014

Physics of Fluids

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Low-frequency unsteadiness of vortices over an ogive-cylinder body was studied using numerical simulation and Dynamic Mode Decomposition (DMD). The results revealed that the vortices over the fore-body of the slender body can exhibit vortex oscillation with a non-dimensional frequency of 0.054 at 70° angle-of-attack, but the flow pattern over the aft-body downstream is Kármán vortex shedding. The vortex oscillation induces larger sectional side-forces on the body than vortex shedding. The DMD analysis for the sectional flow fields at various sections shows that the most energetic mode corresponds to the vortex oscillation at the fore-body and the vortex shedding at the aft-body except the mode for a mean flow, and the associated frequencies are identical to the ones of the sectional side-forces obtained by Fourier transformation.

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Flow Control over a Conical Forebody Using Duty-Cycled Plasma Actuators

Cited by 81 publications

References 20 publications

Preliminary Experimental Study on Aerodynamic Characteristics Control of Slender Body Using DBD Plasma Actuator

Preliminary Experimental Study on Aerodynamic Characteristics Control of Slender Body Using DBD Plasma Actuator

Influence of Plasma Actuations on Forebody Side Forces and Wakes

Low-frequency vortex oscillation around slender bodies at high angles-of-attack

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