Geometry and Aerodynamic Performance of Parabolic Trailing-Edge Flaps

2018 ◽  
Author(s):  
Douglas F. Hunsaker ◽  
Jackson T. Reid ◽  
Bruno Moorthamers ◽  
James J. Joo
Keyword(s):  
Aerodynamic Performance ◽  
Trailing Edge ◽  
Trailing Edge Flaps

Correction: Geometry and Aerodynamic Performance of Parabolic Trailing-Edge Flaps

2018 ◽  
Author(s):  
Douglas F. Hunsaker ◽  
Jackson T. Reid ◽  
Bruno Moorthamers ◽  
James J. Joo
Keyword(s):  
Aerodynamic Performance ◽  
Trailing Edge ◽  
Trailing Edge Flaps

Influence of Flap Deflection Angle on Wind Turbine Airfoil with Trailing Edge Flaps

2014 ◽  
Vol 977 ◽  
pp. 222-227
Author(s):  
Ya Lei Jia ◽  
Zhong He Han ◽  
Fu You Li ◽  
Ya Kai Bai ◽  
Ji Xuan Wang
Keyword(s):  
Wind Turbine ◽  
Deflection Angle ◽  
Aerodynamic Performance ◽  
Main Body ◽  
Trailing Edge ◽  
Trailing Edge Flaps ◽  
Wind Turbine Airfoil ◽  
Trailing Edge Flap ◽  
Flap Deflection ◽  
Drag Ratio

To improve the ability of capturing the wind energy of wind turbine and shorten the design period is of great importance to designing wind turbine blade. The article established S809 airfoil model with trailing edge flaps, The gap of the frontal subject and trailing edge flap adopt uniform gap structure, this structure will reduce the influence of the gap on aerodynamic characteristics.Using the k-ω Two equation turbulence model , the article calculated aerodynamic performance of S809 with 10% chord length trailing edge flaps under different deflecting angles. Results show that gap between the main body and trailing edge flap has little effect on airfoil aerodynamic performance, however, the deflection Angle of Trailing edge flap have great affect on airfoil aerodynamic performance, when deflection Angle of trailing edge flap is 14 ° degrees ,the lift-to-drag ratio is the largest.

Adaptive Neurocontrol of Simulated Rotor Vibrations Using Trailing Edge Flaps

1999 ◽  
Vol 10 (11) ◽  
pp. 855-871
Author(s):  
MICHAEL G. SPENCER ◽  
ROBERT M. SANNER ◽  
INDERJIT CHOPRA
Keyword(s):  
Trailing Edge ◽  
Trailing Edge Flaps

scholarly journals A Parametric Study of Trailing Edge Flap Implementation on Three Different Airfoils Through an Artificial Neuronal Network

Symmetry ◽  
2020 ◽  
Vol 12 (5) ◽  
pp. 828
Author(s):  
Igor Rodriguez-Eguia ◽  
Iñigo Errasti ◽  
Unai Fernandez-Gamiz ◽  
Jesús María Blanco ◽  
Ekaitz Zulueta ◽  
...  
Keyword(s):  
Aerodynamic Coefficients ◽  
Trailing Edge ◽  
High Lift ◽  
Trailing Edge Flaps ◽  
Artificial Neural Network Ann ◽  
Lift And Drag ◽  
Artificial Neuronal Network ◽  
Naca 0012 ◽  
Drag Ratio ◽  
Lift To Drag Ratio

Trailing edge flaps (TEFs) are high-lift devices that generate changes in the lift and drag coefficients of an airfoil. A large number of 2D simulations are performed in this study, in order to measure these changes in aerodynamic coefficients and to analyze them for a given Reynolds number. Three different airfoils, namely NACA 0012, NACA 64(3)-618, and S810, are studied in relation to three combinations of the following parameters: angle of attack, flap angle (deflection), and flaplength. Results are in concordance with the aerodynamic results expected when studying a TEF on an airfoil, showing the effect exerted by the three parameters on both aerodynamic coefficients lift and drag. Depending on whether the airfoil flap is deployed on either the pressure zone or the suction zone, the lift-to-drag ratio, CL/CD, will increase or decrease, respectively. Besides, the use of a larger flap length will increase the higher values and decrease the lower values of the CL/CD ratio. In addition, an artificial neural network (ANN) based prediction model for aerodynamic forces was built through the results obtained from the research.

scholarly journals An investigation of unsteady 3D effects on trailing edge flaps

2016 ◽  
Author(s):  
Eva Jost ◽  
Annette Fischer ◽  
Galih Bangga ◽  
Thorsten Lutz ◽  
Ewald Krämer
Keyword(s):  
Trailing Edge ◽  
Trailing Vortices ◽  
Trailing Edge Flaps ◽  
Negative Effect ◽  
3D Effects ◽  
Computational Fluid Dynamics Cfd ◽  
Trailing Edge Flap ◽  
The Impact ◽  
2D Airfoil ◽  
High Influence

Abstract. The present study investigates the impact of unsteady and viscous 3D aerodynamic effects on a wind turbine blade with trailing edge flap by means of Computational Fluid Dynamics (CFD). Harmonic oscillations are simulated on the DTU 10 MW rotor with a morphing flap of 10 % chord extent ranging from 70 % to 80 % blade radius. The deflection frequency is varied in the range between 1 p and 6 p. To quantify 3D effects, rotor simulations are compared to 2D airfoil computations and the 2D theory by Theodorsen. A significant influence of trailing and shed vortex structures has been found which leads to an amplitude reduction and hysteresis of the lift response in the flap section with regard to the deflection signal. For the 3D rotor results greater amplitude reductions and a less pronounced hysteresis is observed compared to the 2D airfoil case. Blade sections neighboring the flap experience however an opposing impact and hence partly compensate the negative effect of trailing vortices in the flap section in respect to integral loads. The comparison to steady flap deflections at the 3D rotor revealed the high influence of dynamic inflow effects.

scholarly journals Pressure Based Lift Estimation and its Application to Feedforward Load Control employing Trailing Edge Flaps

2020 ◽  
Author(s):  
Sirko Bartholomay ◽  
Tom T. B. Wester ◽  
Sebastian Perez-Becker ◽  
Simon Konze ◽  
Christian Menzel ◽  
...  
Keyword(s):  
Surface Pressure ◽  
Feedforward Control ◽  
Force Balance ◽  
Estimation Methods ◽  
Load Control ◽  
Trailing Edge ◽  
Trailing Edge Flaps ◽  
Feedforward Controller ◽  
Trailing Edge Flap ◽  
C 30

Abstract. This experimental load control study presents results of an active trailing edge flap feedforward controller for wind turbine applications. The controller input is derived from pressure based lift estimation methods that rely either on a quasi-steady method, based on a three-hole probe, or on an unsteady method that is based on three selected surface pressure ports. Furthermore, a standard feedback controller, based on force balance measurements, is compared to the feedforward control. A Clark-Y airfoil is employed for the wing that is equipped with a trailing edge flap of x/c = 30 % chordwise extension. Inflow disturbances are created by a two-dimensional active grid. The Reynolds number is Re = 290,000 and reduced frequencies of k = 0.07 up to k = 0.32 are analyzed. Within the first part of the paper, the lift estimation methods are compared. The surface pressure based method shows generally more accurate results whereas the three-hole probe estimate overpredicts the lift amplitudes with increasing frequencies. Nonetheless, employing the latter as input to the feedforward controller is more promising as a beneficial phase lead is introduced by this method. A successful load alleviation was achieved up to reduced frequencies of k = 0.192.

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