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Research Papers: Techniques and Procedures

Lift Augmentation Based on Flap Deflection With Dielectric Barrier Discharge Plasma Flow Control Over Multi-Element Airfoils

[+] Author and Article Information
Leilei Yang

School of Aeronautics,
Northwestern Polytechnical University,
No. 127, West Youyi Road,
Xi'an 710072, China
e-mail: rainyon@mail.nwpu.edu.cn

Jiang Li

Beijing Aeronautical Science
and Technology Research Institute,
Future Technology Park,
Changping, Beijing 102211, China
e-mail: lijiang@comac.cc

Jinsheng Cai

School of Aeronautics,
Northwestern Polytechnical University,
No. 127, West Youyi Road,
Xi'an 710072, China
e-mail: caijsh@nwpu.edu.cn

Guangqiu Wang

Beijing Aeronautical Science
and Technology Research Institute,
Future Technology Park,
Changping, Beijing 102211, China
e-mail: wangguangqiu@comac.cc

Zhengke Zhang

School of Aeronautics,
Northwestern Polytechnical University,
No. 127, West Youyi Road,
Xi'an 710072, China
e-mail: zkzhang@nwpu.edu.cn

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received May 5, 2015; final manuscript received August 30, 2015; published online October 27, 2015. Assoc. Editor: Shizhi Qian.

J. Fluids Eng 138(3), 031401 (Oct 27, 2015) (10 pages) Paper No: FE-15-1313; doi: 10.1115/1.4031613 History: Received May 05, 2015; Revised August 30, 2015

The effect of the lift augmentation of multi-element airfoils with increased flap deflection and dielectric barrier discharge (DBD) plasma flow control on the flap at several angles of attack (AOAs) is investigated numerically and experimentally. A phenomenological body force model is employed to simulate the DBD actuators at Re = 1.03 × 106. The simulation results show that the atmospheric plasma generated by the DBD actuators completely suppresses the flow separation over the flap at several AOAs, and consequently, the lift augmentation of a multi-element airfoil can be achieved over the entire prestall AOA range. A corresponding flow control experiment on a multi-element airfoil performed in a low-speed wind tunnel at a freestream velocity of 30 m/s is presented; in this experiment, particle image velocimetry (PIV) was employed for flow visualization over the upper surface of the flap. The PIV results demonstrate that the flow separation on the flap is suppressed completely by the same DBD actuators used in the simulation.

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References

Figures

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Fig. 5

CP distributions on the surface of the 30P30N multi-element airfoil for Ma = 0.2 and Re = 9 × 106: (a) α = 4 deg and (b) α = 8 deg

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Fig. 9

The pressure coefficient distributions on the main element and the flap of the 30P35N airfoil in the plasma-off and plasma-on cases for (a) α = 0 deg, (b) α = 4 deg, (c) α = 8 deg, and (d) α = 12 deg

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Fig. 10

Layout of the 30P35N airfoil model and the PIV system in the wind tunnel test section

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Fig. 11

The flow-field zone photographed by the PIV system

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Fig. 12

Array of six SDBD actuators: (a) schematic top view, (b) schematic side view, and (c) layout on the flap

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Fig. 13

Computational fluid dynamics (CFD) results and PIV flow visualizations focusing on the upper surface of the flap of the 30P35N airfoil at a freestream velocity of 30 m/s for (a) α = 0 deg, (b) α = 4 deg, (c) α = 8 deg, and (d) α = 12 deg

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Fig. 6

Aerodynamic characteristics of 30P22N, 30P30N, and 30P35N with no plasma actuation: (a) lift coefficient versus AOA, (b) drag coefficient versus AOA, and (c) lift-to-drag ratio versus AOA

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Fig. 4

The C-type structured mesh employed for the numerical simulations

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Fig. 3

Model geometry and nomenclature for the McDonnell Douglas Aerospace (MDA) 2D three-element airfoil

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Fig. 2

Comparison of velocity profiles at four locations on the plate between the present paper and Ref. [26]

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Fig. 1

△OAB forms the plasma-induced body force region in the phenomenological model

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Fig. 7

Comparison of the aerodynamic characteristics of the 30P35N airfoil in the plasma-on case with those of both the 30P30N and 30P35N models in the plasma-off case: (a) lift coefficient versus AOA, (b) drag coefficient versus AOA, and (c) lift-to-drag ratio versus AOA

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Fig. 8

Comparison of the flow patterns around the 30P35N airfoil at: (a) α = 4 deg in the plasma-off case, (b) α = 4 deg in the plasma-on case, (c) α = 12 deg in the plasma-off case, and (d) α = 12 deg in the plasma-on case

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