Control of the dynamic-stall vortex over a pitching airfoil by leading-edge suction

Karim, Md. Ahsanul; Acharya, Mukund

doi:10.2514/6.1993-3267

Cited by 12 publications

(16 citation statements)

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“…Activeleading-edge suction (Karim and Acharya, 1993), passive suction (Addington, et al, 1992), and leading-edge slats (Carr and McAlister, 1983) have all been shown to suppress dynamic stall to varying degrees. In addition, air blown tangentially and perpendicularly (Luttges, et al, 1985) over the suction surface have also demonstrated beneficial control effects.…”

Section: -1mentioning

confidence: 99%

“…A compressible Navier-Stokes code (Visbal, 1986a) written, well validated, and used by Visbal for several numerical studies on dynamic stall (Visbal, 1991;1990a;1990b;1986b;Visbal and Shang, 1989;) is used at low Mach numbers. In addition to investigation of tangential blowing effects on dynamic stall, results are presented from a brief study of leading-edge (0.05c) suction 1-3 (after experimental work of Karim and Acharya (1993). Based on these studies, a control strategy is recommended.…”

Section: -1mentioning

confidence: 99%

“…Addington et al (1992) were able to suppress dynamic stall at low pitch rates (0+ < 0.05) using passive suction. Suction at a volume flow rate greater than or equal to the rate of fluid accumulation under the leading-edge shear layer was found to be extremely successful for suppressing dynamic stall vortex formation (Karim and Acharya, 1993).…”

Section: Ezperimental and Computationalmentioning

confidence: 99%

“…Experimental (Karim and Acharya, 1993;Freymuth, et al, 1989;Carr and McCalister, 1983) and computational (Ghia, et al, 1992;Visbal, 1991) studies have demonstrated the utility of control devices (suction, moving wall, leading-edge slat) placed in the leading-edge area where the dynamic-stall vortex forms. Experimental studies (Lovato and Troutt,(4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15)(16)(17) 1992) have also shown some benefit to pulsed blowing simultaneously through multiple slots located at 0.0c, 0.2c, and 0.4c.…”

Section: Slot-location and Width Effectsmentioning

confidence: 99%

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Numerical simulation of dynamic-stall suppression by tangential blowing

Towne

1994

32nd Aerospace Sciences Meeting and Exhibit

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Section: -1mentioning

confidence: 99%

Section: -1mentioning

confidence: 99%

Section: Ezperimental and Computationalmentioning

confidence: 99%

Section: Slot-location and Width Effectsmentioning

confidence: 99%

See 2 more Smart Citations

Numerical simulation of dynamic-stall suppression by tangential blowing

Towne

1994

32nd Aerospace Sciences Meeting and Exhibit

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“…Flow separation control is currently employed via vortex generators on the wings of most Boeing aircrafts. It is also used via blown flaps on older generation supersonic fighters or leading-edge extensions and strokes on newer generations [12][13][14] .…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Flow Control by Suction and Injection on a Subsonic Airfoil

Shojaefard¹,

Noorpoor²,

Avanesians³

et al. 2005

American J. of Applied Sciences

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This study presents a numerical study concerning flow control by suction and injection. The case studied is the flow field over a subsonic airfoil with four suction and injection slots on the suction side of the airfoil. Five different angles of attack, 0, 5, 10, 13.3 and 20 with the Mach number of 0.15 are studied. Three cases are studied in each angle of attack. The three cases are airfoil with surface suction, surface injection and the base airfoil. A commercial CFD code, the FLUENT, is used in this study. The effect of suction and injection on aerodynamic coefficients is investigated. The results show that the surface suction can significantly increase the lift coefficient. The injection decreases the skin friction.

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Physics of Dynamic Stall Vortex During Pitching Oscillation of Dynamic Airfoil

Wei

Gao

2021

Int. J. Aeronaut. Space Sci.

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Dynamic stall, which has a significant effect on the aerodynamic performances of dynamic airfoils, is closely related to the physics of the dynamic stall vortex (DSV). The physics of the DSV on the NACA 0012 airfoil was experimentally studied using unsteady pressure measurements with high time accuracy. The experimental Reynolds number was Re = 1.5 × 106, and the reduced frequency was k = 0.069. The propagation of the unsteady pressure field during the dynamic stall process was analyzed in detail. The motion characteristics of the DSV were examined, including its near-wall development characteristics and near-wall evolution velocity. Moreover, the frequency characteristics of the near-wall DSV were studied using wavelet analysis combined with proper orthogonal decomposition (POD) technology. In addition, the effects of the mean angle of attack (AoA) and the amplitude on the DSV motion and frequency characteristics were examined in detail. The effects of the mean AoA on the near-wall DSV strength and the propagation velocity were linear, while the effects of amplitude were nonlinear. The mean AoA and amplitude had a significant influence on the frequency of the leading-edge vortex (LEV) at the initial stage of the DSV development (x/c = 0.10–0.20). This work allows the DSV physics to be understood more deeply. Graphic abstract

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Control of the dynamic-stall vortex over a pitching airfoil by leading-edge suction

Cited by 12 publications

References 1 publication

Numerical simulation of dynamic-stall suppression by tangential blowing

Numerical simulation of dynamic-stall suppression by tangential blowing

Numerical Investigation of Flow Control by Suction and Injection on a Subsonic Airfoil

Physics of Dynamic Stall Vortex During Pitching Oscillation of Dynamic Airfoil

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