Enhanced Aerofoil Performance Using Small Trailing-Edge Flaps

Bloy, A. W.; Tsioumanis, Nick; Mellor, N. T.

doi:10.2514/2.2210

Cited by 23 publications

(11 citation statements)

References 1 publication

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“…Figure 10 has shown the chordwise pressure coefficient distribution on the upper and lower surface of the wing with different deflecting angles ( = 2.4%c and = 0.6). As shown in Figure 10(a), for the nonaileron case, the chordwise pressure coefficient distribution has shown the same trend as the conventional airfoil theory [14][15][16]; that is, the higher pressure region is on the lower surface of the wing and the lower pressure region is on the upper surface of wing.…”

Section: Effects Of the Different Deflecting Anglesmentioning

confidence: 53%

Investigation of the Three-Dimensional Hinge Moment Characteristics Generated by the ONERA-M6 Wing with an Aileron

Zhang

Chien

2013

Advances in Mechanical Engineering

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The hinge moment characteristics for ONERA-M6 wing with aileron configuration have been investigated numerically based on the different gaps and deflecting angles. The results show that the effects on the wing made by the deflecting aileron are notable. Comparing with the nonaileron case, the chordwise pressure coefficient distribution for the wing with aileron has shown the totally different trends. The small gap can force the air flow through and form the extremely strong spraying flow. It can directly destroy the previously formed leading edge vortex (LEV). Due to the presence of the positive deflecting angle, the trailing edge vortex (TEV) will begin to generate at the trailing edge of the aileron. The induced secondary LEV will be mixed with the developing TEVs and form the stronger TEVs at the downstream position. Comparing with the subsonic flow, the curve for the supersonic flow has shown a good linear. The corresponding hinge moments are also extremely sensitive to the changing angle of attack, and the slope of curves is also bigger than that of the subsonic flow. The bigger gap and deflecting angle can result in the curve of hinge moment bending upward at high angle of attack. The corresponding pressure cloud and streamlines have also been obtained computationally and analyzed in detail.

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Section: Effects Of the Different Deflecting Anglesmentioning

confidence: 53%

Investigation of the Three-Dimensional Hinge Moment Characteristics Generated by the ONERA-M6 Wing with an Aileron

Zhang

Chien

2013

Advances in Mechanical Engineering

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“…The drag of the tested 2% c wedge flap at a 45° angle with a Cl of 1.0 was approximately 10% lower than with a miniflap at a 45° deflection angle (Fig. 14) (Bloy et al 1997).…”

Section: Future Workmentioning

confidence: 92%

“…When using airfoil NACA 5414, Cl 1.0 increased at the miniflap of 2% C and fixed angle of 45° from Cm = -0.122 to 0.225 ( Fig. 4) (Bloy et al 1997).…”

Section: Introductionmentioning

confidence: 90%

Influence of Miniflaps on Sailplane Flight Characteristics

Lauk

Unt

2015

Aviation

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The effect of miniflaps for increasing the L/D ratio and the lift coefficient has been studied on airliners as well as on UAV-s and wind turbines. For sailplanes the lift when Cl > 1.0 is of main interest. As the maximum wing loading of racing sailplanes reaches 60–62 kg/m2, it is necessary to achieve a high Cl max (1.7–1.8) in thermals. In this case the decrease in TAS caused by a high Cl max even compensates for the drop of the L/D ratio to a certain extent, as the climb speed will increase when the spiral flight radius diminishes in thermals. To bring the L/D to Cl > 1.0, a 2% chord miniflap at a 30° deflection angle was attached to the trailing edge of a Jantar-Standard 3 type sailplane wing (airfoil NN-8). In flight tests it was found that the miniflap increased the sailplane‘s Cl max to 1.35–1.66, i.e. by 23% (Re 1.0–0.92×106). At the same time the L/D ratio Cl increased by over 1.0. Especially good L/D improvement was noted with Cl at 1.13–1.19. In thermal Cl of 1.57–1.65 the roll control was good. At lower Cl < 1.0 values, the miniflap reduced the L/D ratio in comparison with a normal configuration.

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“…It was shown first by Liebeck 7 that a Newman airfoil with 1.25% chord GF resulted in an increase in lift and a certain reduction in zero-lift angle of attack, and the GF is successfully used to control flow over airfoil by many researchers. [8][9][10][11][12] The results show that the GF can increase the lift and the maximum lift coefficient with slight changes in the stalling incidence.…”

Section: Introductionmentioning

confidence: 99%

Airfoil flow control using vortex generators and a Gurney flap

Hao

Gao

Song

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part C:

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In order to carry out the experimental investigation on control of flow over airfoil, one form of the Gurney flap and one form of the vortex generator were designed. The comparative study is performed for different scenarios such as clean airfoil, clean airfoil with Gurney flap, clean airfoil with vortex generators and clean airfoil with both Gurney flap and vortex generators. Wind tunnel test shows that: (a) the lift at linear regime with the same attack is greatly increased by using a Gurney flap; (b) the stall performance is remarkably improved by using vortex generators; and (c) the lift at both linear and stall regimes are both improved by using combined Gurney flap and vortex generators, and drag is slightly increased at linear regime and greatly reduced at stall regime. In other words, the proper combination of Gurney flap and vortex generators can result in remarkable improvement of aerodynamic performance of an airfoil, and it is an ideal combinational control style.

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Enhanced Aerofoil Performance Using Small Trailing-Edge Flaps

Cited by 23 publications

References 1 publication

Investigation of the Three-Dimensional Hinge Moment Characteristics Generated by the ONERA-M6 Wing with an Aileron

Investigation of the Three-Dimensional Hinge Moment Characteristics Generated by the ONERA-M6 Wing with an Aileron

Influence of Miniflaps on Sailplane Flight Characteristics

Airfoil flow control using vortex generators and a Gurney flap

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