A new airfoil design method for wind turbine to improve maximum lift of airfoil

2021 ◽  
pp. 0309524X2098442
Author(s):  
Qing Wang ◽  
Deshun Li
Keyword(s):  
Wind Turbine ◽  
Lift Force ◽  
Rotation Angle ◽  
Design Method ◽  
Angle Of Attack ◽  
Scale Factor ◽  
High Angle ◽  
High Angle Of Attack ◽  
Wind Turbine Airfoil ◽  
Force Characteristics

A new wind turbine airfoil design method is established. This method generates an airfoil by fusing different airfoils. The airfoil designed by this method could restrict the airflow separation near the trailing edge of airfoil at high angle of attack, meanwhile the turbulence also is restricted. As a result, the maximum lift force is increased about 16.4% at high angle of attack. Meanwhile, the drag force is decreased about 31.3%. By analyzing the influence of scale factor and rotation angle on the airfoil aerodynamic force characteristics, the simulated results indicate that the larger scale factor and rotation angle could increase the lift stall angle and the maximum lift force. Therefore, this method could be used for designing wind turbine airfoil with high maximum lift force characteristics.

The Aerodynamics Investigation of Vortex Trap on Helicopter Blade

2012 ◽  
Vol 225 ◽  
pp. 43-48
Author(s):  
M.F. Yaakub ◽  
A.A. Wahab ◽  
Mohammad Fahmi Abdul Ghafir ◽  
Siti Nur Mariani Mohd Yunos ◽  
Siti Juita Mastura Mohd Salleh ◽  
...  
Keyword(s):  
Lift Force ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Strong Wind ◽  
High Angle ◽  
Forward Flight ◽  
High Angle Of Attack ◽  
Helicopter Blade ◽  
Stall Angle ◽  
Cfd Analyses

During helicopter forward flight, the retreating blade revolves at high angle of attack compared to advancing blade in order to balance the lift and also to stabilise the helicopter. However, due to the aerodynamics limitations of the retreating blade at forward flight, stall may occur at high angle of attack compared with the advancing blade. This phenomenon is dangerous for pilot when controlling and balancing the helicopter while flying against strong wind. This paper investigates the capabilities of introducing multiple vortex traps on the upper surface of the helicopter airfoil in order to delay the stall angle of retreating helicopter blade. Blade Element Theory (BET) was applied to scrutinize the lift force along the helicopter blade. Computational Fluid Dynamic (CFD) analyses using the Shear-Stress Transport (SST) turbulence model was carried out to investigate the effect of groove on delaying the stall and to predict the separation of flow over the airfoil. Based on the CFD analyses, the optimization of the groove was done by analyzing the numbers and locations of the grooves. Finally, the results from both BET and the CFD analyses were utilised to obtain the lift force achieved by the vortex trap. The study showed that the presence of multiple vortex traps has successfully increased the lift coefficient and most importantly, delaying the stall angle.

Plasma Flow Control Simulation of an Airfoil of Wind Turbine at an Intermediate Reynolds Number

2013 ◽  
Author(s):  
Hikaru Aono ◽  
Taku Nonomura ◽  
Aiko Yakeno ◽  
Kozo Fujii ◽  
Koichi Okada
Keyword(s):  
Reynolds Number ◽  
Flow Control ◽  
Wind Turbine ◽  
Shear Layer ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Dominant Factor ◽  
High Angle ◽  
High Angle Of Attack

The flow over a National Renewable Energy Laboratory S825 airfoil was simulated for a chord Reynolds number of 7.5×105 and an angle of attack of 22.1 deg. These conditions approximately matched a blade element condition of 75% radius of 42-m-diameter wind turbine operating 2.5 rpm under a free-stream of 10 m/s. Computed flow of the uncontrolled case characterized massive separation from near the leading edge due to high angle of attack. With the active flow control by a dielectric barrier discharge plasma actuator, separation was reduced and the lift-to-drag ratio increased from 2.25 to 6.52. Impacts of the plasma actuator on the shear layer near the leading edge were discussed. Direct momentum addition provided by the case setup of plasma actuator considered in current study seemed to be a dominant factor to prevent the separation of shear layer near the leading edge rather than influence of small disturbances induced by the plasma actuator operated in a burst modulation. However, due to the high angle of attack and the thick airfoil, the control authority of the plasma actuator with the setup (i.e. the operating condition and number of plasma actuators installed on the wing surface) considered was insufficient to completely suppress the separation over the NREL S825 airfoil.

scholarly journals Leading Edge Blowing to Mimic and Enhance the Serration Effects for Aerofoil

2021 ◽  
Vol 11 (6) ◽  
pp. 2593
Author(s):  
Yasir Al-Okbi ◽  
Tze Pei Chong ◽  
Oksana Stalnov
Keyword(s):  
Boundary Layer ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Boundary Layer Separation ◽  
Shear Instability ◽  
Vortical Flow ◽  
High Angle ◽  
High Angle Of Attack ◽  
Layer Separation ◽  
Aerodynamic Performances

Leading edge serration is now a well-established and effective passive control device for the reduction of turbulence–leading edge interaction noise, and for the suppression of boundary layer separation at high angle of attack. It is envisaged that leading edge blowing could produce the same mechanisms as those produced by a serrated leading edge to enhance the aeroacoustics and aerodynamic performances of aerofoil. Aeroacoustically, injection of mass airflow from the leading edge (against the incoming turbulent flow) can be an effective mechanism to decrease the turbulence intensity, and/or alter the stagnation point. According to classical theory on the aerofoil leading edge noise, there is a potential for the leading edge blowing to reduce the level of turbulence–leading edge interaction noise radiation. Aerodynamically, after the mixing between the injected air and the incoming flow, a shear instability is likely to be triggered owing to the different flow directions. The resulting vortical flow will then propagate along the main flow direction across the aerofoil surface. These vortical flows generated indirectly owing to the leading edge blowing could also be effective to mitigate boundary layer separation at high angle of attack. The objectives of this paper are to validate these hypotheses, and combine the serration and blowing together on the leading edge to harvest further improvement on the aeroacoustics and aerodynamic performances. Results presented in this paper strongly indicate that leading edge blowing, which is an active flow control method, can indeed mimic and even enhance the bio-inspired leading edge serration effectively.

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