Dynamic stall control over an airfoil by NS-DBD actuation

doi:10.1088/1674-1056/abb227

Abstract

The wind tunnel test was conducted with an NACA 0012 airfoil to explore the flow control effects on airfoil dynamic stall by NS-DBD plasma actuation. Firstly, light and deep dynamic stall states were set, based on the static stall characteristics of airfoil at a Reynolds number of 5.8 × 10⁵. Then, the flow control effect of NS-DBD on dynamic stall was studied and the influence law of three typical reduced frequencies (k = 0.05, k = 0.05, and k = 0.15) was examined at various dimensionless actuation frequencies (F⁺ = 1, F⁺ = 2, and F⁺ = 3). For both light and deep dynamic stall states, NS-DBD had almost no effect on upstroke. However, the lift coefficients on downstroke were increased significantly and the flow control effect at F⁺ = 1 is the best. The flow control effect of the light stall state is more obvious than that of deep stall state under the same actuation conditions. For the same stall state, with the reduced frequency increasing, the control effect became worse. Based on the in being principles of flow separation control by NS-DBD, the mechanism of dynamic stall control was discussed and the influence of reduced frequency on the dynamic flow control was analyzed. Different from the static airfoil flow separation control, the separated angle of leading-edge shear layer for the airfoil in dynamic stall state is larger and flow control with dynamic oscillation is more difficult. The separated angle is closely related to the effective angle of attack, so the effect of dynamic stall control is greatly dependent on the history of angles of attack.

Keywords: flow control dynamic stall dielectric barrier discharge (DBD) nanosecond pulse reduced frequency

Received: 03 July 2020
Revised: 06 August 2020
Accepted manuscript online: 25 August 2020

PACS:	52.30.-q	(Plasma dynamics and flow)
	47.85.ld	(Boundary layer control)
	47.20.Ib	(Instability of boundary layers; separation)
	47.32.Ff	(Separated flows)

Corresponding Authors: ^†Corresponding author. E-mail: zym19860615@163.com ^‡Corresponding author. E-mail: lianghua82702@126.com

About author:

†Corresponding author. E-mail: zym19860615@163.com

‡Corresponding author. E-mail: lianghua82702@126.com

* Project supported by the National Natural Science Foundation of China (Grant No. 11802341) and the Open Fund from State Key Laboratory of Aerodynamics of China (Grant No. SKLA20180207).

Cite this article:

He-Sen Yang(杨鹤森), Guang-Yin Zhao(赵光银)†, Hua Liang(梁华)‡, and Biao Wei(魏彪) Dynamic stall control over an airfoil by NS-DBD actuation 2020 Chin. Phys. B 29 105203

Fig. 1.

Flow field of airfoil dynamic stall within a pitch period.^[13]

Fig. 2.

Airfoil installation and experimental layout in wind tunnel.

Fig. 3.

Airfoil oscillation drive device.

Fig. 4.

Deployment of actuator at the leading edge of airfoil and electrical parameter measurement: (a) deployment of actuator. (b) system of electrical parameter measurement.

Fig. 5.

Characteristics of NS-DBD in still air: (a) voltage and current curves of NS-DBD (V_{p – p} = 13 kV), (b) discharge image of NS-DBD, and (c) shock wave induced by NS-DBD experimental results.

Fig. 6.

Static experimental lift coefficient C_L under different airfoil’s profile states.

Table 1.

List of dynamic stall states.

Fig. 7.

Baseline for various reduced frequencies of light dynamic stall.

Fig. 8.

Flow control effects under light stall state (k = 0.05).

Fig. 9.

Flow control effects under light stall state (k = 0.1).

Fig. 10.

Flow control effects under light stall state (k = 0.15).

Fig. 11.

Baseline for various reduced frequencies of deep dynamic stall.

Fig. 12.

Flow control effects under deep stall state (k = 0.05).

Fig. 13.

Flow control effects under deep stall state (k = 0.1).

Fig. 14.

Flow control effects under deep stall state (k = 0.15).

Fig. 15.

Flow field over a static airfoil with and without NS-DBD:^[30] (a) plasma off and (b) plasma on.

Fig. 16.

Flow field with and without actuation for dynamic stall: (a) base flow field at high α, (b) flow field with actuation at high α, (c) flow field with actuation when airfoil pitching down to a certain degree.

Fig. 17.

Analysis for effect of various k at certain α on downstroke: (a) k = 0.05 pitch-down motion, (b) k = 0.1 pitch-down motion, and (c) k = 0.15 pitch-down motion.

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