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Guangyin Zhao
Air Force Engineering University
Corresponding Author
ORCiD: https://orcid.org/0000-0003-1545-1747
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At present, the control capability of dielectric barrier discharge (DBD) plasma actuation covers the flow velocity range of helicopter’s retreating blades, so it is necessary to extend it to the dynamic stall control of rotor airfoils. A DBD plasma actuator was adopted to control the dynamic stall of an oscillating CRA309 airfoil in this paper. The effectiveness of alternating current (AC) DBD plasma actuation on reducing the area of lift hysteresis loop of the oscillating airfoil was verified through pressure measurements at a Reynolds number of 5.2×105. The influence of actuation parameters on the airfoil’s lift and moment coefficients was studied. Both steady and unsteady actuation could effectively reduce the hysteresis loop area of the lift coefficients. The flow control effect of dynamic stall was strongly dependent on the history of angle of attack. Compared with the steady actuation, unsteady actuation had more obvious advantages in dynamic stall control, with reducing the area of lift hysteresis loop by more than 30%. The effects of plasma actuation on the airfoil’s flow field at both upward and downward stages were discussed at last.
Keywords
Plasma flow control, Flow separation, Dynamic stall, Hysteresis, Dielectric barrier discharge
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View the published article at Advances in Aerodynamics.
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On 17 Nov, 2020
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Received 11 Nov, 2020
Reviewer #2 agreed
On 06 Nov, 2020
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Reviewer #1 agreed
On 25 Oct, 2020
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A new preprint design is coming!
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See the published version of this preprint at Advances in Aerodynamics.
This is a preprint, a preliminary version of a manuscript that has not completed peer review at a journal. Research Square does not conduct peer review prior to posting preprints. The posting of a preprint on this server should not be interpreted as an endorsement of its validity or suitability for dissemination as established information or for guiding clinical practice.
Learn more about In Review
Research
Guangyin Zhao
Air Force Engineering University
Corresponding Author
ORCiD: https://orcid.org/0000-0003-1545-1747
Badges
Prescreen
This manuscript passed our Prescreen assessment
Complete author information
Appropriate declaration statements
Potential risks to human health
Prescreen
Peer Review Timeline
CURRENT STATUS: Published
View the published article at Advances in Aerodynamics.
Version 1
Posted 27 Oct, 2020
No community comments so far
Editorial decision: Minor revision
On 06 Dec, 2020
Review #3 received
Received 05 Dec, 2020
Review #2 received
Received 19 Nov, 2020
Reviewer #3 agreed
On 17 Nov, 2020
Review #1 received
Received 11 Nov, 2020
Reviewer #2 agreed
On 06 Nov, 2020
Reviewers invited
Invitations sent on 25 Oct, 2020
Reviewer #1 agreed
On 25 Oct, 2020
Editor assigned
On 23 Oct, 2020
Submission checks complete
On 22 Oct, 2020
Editor invited
On 22 Oct, 2020
First submitted
On 21 Oct, 2020
Metrics
Comments: 0
PDF Downloads: ...
HTML Views: ...
Subject Areas
Aeronautics and Astronautics
License:
This work is licensed under a CC BY 4.0 License. Read Full License
View the published article at Advances in Aerodynamics.
At present, the control capability of dielectric barrier discharge (DBD) plasma actuation covers the flow velocity range of helicopter’s retreating blades, so it is necessary to extend it to the dynamic stall control of rotor airfoils. A DBD plasma actuator was adopted to control the dynamic stall of an oscillating CRA309 airfoil in this paper. The effectiveness of alternating current (AC) DBD plasma actuation on reducing the area of lift hysteresis loop of the oscillating airfoil was verified through pressure measurements at a Reynolds number of 5.2×105. The influence of actuation parameters on the airfoil’s lift and moment coefficients was studied. Both steady and unsteady actuation could effectively reduce the hysteresis loop area of the lift coefficients. The flow control effect of dynamic stall was strongly dependent on the history of angle of attack. Compared with the steady actuation, unsteady actuation had more obvious advantages in dynamic stall control, with reducing the area of lift hysteresis loop by more than 30%. The effects of plasma actuation on the airfoil’s flow field at both upward and downward stages were discussed at last.
Figure 1
Figure 2
Figure 3
Figure 4
Figure 5
Figure 6
Figure 7
Figure 8
Figure 9
Figure 10
The full text of this article is available to read as a PDF.
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