Computational Investigation of the Effects of Gurney Flap on the Aerodynamic Performance of VR-12 Airfoil

Guzel, Goktan; Sankar, Lakshmi N.; Rhee, Myung

doi:10.2514/6.2005-4960

Cited by 9 publications

(4 citation statements)

References 6 publications

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“…For 2-D airfoils with Gurney flaps [6,7,[32][33][34], Fig. 10 indicates that the pitch/lift ratio tends to be slightly less than this theoretical value.…”

Section: Pitching Momentmentioning

confidence: 60%

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Gurney Flaps on Slender and Nonslender Delta Wings

Greenwell

2010

Journal of Aircraft

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A parametric low-speed wind-tunnel study has been undertaken of the effects of Gurney flap height on the aerodynamic characteristics of delta wings with sweep angles of 40, 60, and 70 . Flap effects on lift and drag are consistent with previous two-dimensional data when wing geometry is accounted for by using the change in zero-lift incidence rather than lift and using the relative flap area rather than flap height. Flap deployment primarily affects the attached-flow potential lift on delta wings, with vortex lift being almost unchanged. Induced-drag factors are considerably reduced as flap height is increased, but this is due to the use of flat-plate models with near-zero leadingedge suction. For control applications, pitch/lift ratios are similar to those for delta wings with conventional trailingedge flaps, but the trim-drag penalties are much higher. An aft shift in loading associated with Gurney flap deployment leads to large aft movements of the aerodynamic center, which significantly reduces control capability.pitching-moment coefficient at zero lift C N = normal force coefficient, N=qS C NP = potential flow component of normal force C NV = vortex lift component of normal force D = drag h = projected flap height (measured from lower surface) K P = potential lift factor, C L K V = vortex lift factor k = induced-drag factor, C D C D min AR=C 2 L L = lift q = dynamic pressure, 1 2 V 2 q = lift increase factor on flap height S = wing area S f = flap frontal area, hb t = wing thickness = angle of attack 0L = zero-lift angle of attack 0P = zero-lift angle of attack for potential lift component 0V = zero-lift angle of attack for vortex lift component = leading-edge sweep angle

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“…For 2-D airfoils with Gurney flaps [6,7,[32][33][34], Fig. 10 indicates that the pitch/lift ratio tends to be slightly less than this theoretical value.…”

Section: Pitching Momentmentioning

confidence: 60%

“…The filled symbols denote increments derived from the Bristol data of [26,27], and the open diamond symbols denote a rectangular wing with an aspect ratio of 6 [31]. The crosses show data for a range of 2-D airfoils with Gurney flaps [6,7,[32][33][34]. The same symbols are used in the following figures.…”

Section: A Liftmentioning

confidence: 96%

Gurney Flaps on Slender and Nonslender Delta Wings

Greenwell

2010

Journal of Aircraft

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“…The present authors have recently studied the steady and unsteady load characteristics of a VR-12 airfoil with and without the Gurney flap [2]. It was found that the use of a Gurney flap could improve the static lift characteristics giving rise to a higher C l;max (close to 1.8) compared to the conventional airfoil (close to 1.4).…”

Section: Introductionmentioning

confidence: 99%

Computational Investigation of Gurney Flap Effects on Rotors in Forward Flight

Min

Sankar

Rajmohan

et al. 2009

Journal of Aircraft

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A hybrid Navier-Stokes/free-wake solver has been employed to investigate the performance of a rotor equipped with a Gurney flap in steady level flight and in descent. A scaled model of the BO-105 rotor was studied. The calculations were coupled to a comprehensive analysis to properly account for the effects of the elastic deformations on the aerodynamic loads and to account for trim. Fixed and dynamically deployed Gurney flaps were considered. In forward flight, it was found that a properly chosen azimuthal deployment schedule of the Gurney flaps may reduce the peak-to-peak variations in hub loads, potentially reducing vibrations. In descent flight, it was found that the deployment of a fixed Gurney flap decreased the descent rate needed to maintain autorotation.

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“…Gurney flaps have been widely used and studied in airfoil static/dynamic stall control [2][3][4][5], flutter control [6], flapping airfoil control [7], ground effects [8], and rotor blade load control [9][10][11][12][13]. In these applications, the increases in the lift and the drag are closely related to airfoils, flow conditions, and the flap geometry.…”

Section: Introductionmentioning

confidence: 99%

Effect of Gurney Flap Geometry on a S809 Airfoil

Hao

Gao

2019

International Journal of Aerospace Engineering

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In this paper, the effect of Gurney flap shapes on wind turbine blade airfoil S809 has been studied by numerical simulation. First, the O-type grid is used in the numerical simulation. By comparing with experimental data, such as the lift force, the drag coefficient, and the pressure distribution, the accuracy of the simulation method is validated. Second, the research on the widths of three kinds of rectangular Gurney flaps at the trailing edge of the S809 airfoil is carried out. Rectangular Gurney flaps can considerably increase the lift in both the linear and nonlinear sections, and the maximum lift coefficient can be increased by 20.65%. In addition, the drag and the pitching moment are increased. However, the width of the rectangular Gurney flap has a small impact on the lift, the drag, and the pitching moment. Finally, the effects of rectangular and triangular Gurney flaps on the aerodynamic characteristics of the S809 airfoil are compared. The results show that the triangular flaps can obtain an increase of maximum lift coefficient by 28.42%, which is better than 16.31% of the rectangular flaps.

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Computational Investigation of the Effects of Gurney Flap on the Aerodynamic Performance of VR-12 Airfoil

Cited by 9 publications

References 6 publications

Gurney Flaps on Slender and Nonslender Delta Wings

Gurney Flaps on Slender and Nonslender Delta Wings

Computational Investigation of Gurney Flap Effects on Rotors in Forward Flight

Effect of Gurney Flap Geometry on a S809 Airfoil

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