scholarly journals Corrigendum to “Propagation of Shock on NREL Phase VI Wind Turbine Airfoil under Compressible Flow”

2016 ◽  
Vol 2016 ◽  
pp. 1-1
Author(s):  
Mohammad A. Hossain ◽  
Ziaul Huque ◽  
Raghava R. Kommalapati
Keyword(s):  
Wind Turbine ◽  
Compressible Flow ◽  
Wind Turbine Airfoil ◽  
Nrel Phase Vi

scholarly journals Propagation of Shock on NREL Phase VI Wind Turbine Airfoil under Compressible Flow

2013 ◽  
Vol 2013 ◽  
pp. 1-9 ◽  
Author(s):  
Mohammad A. Hossain ◽  
Ziaul Huque ◽  
Raghava R. Kammalapati
Keyword(s):  
Shock Waves ◽  
Wind Turbine ◽  
Compressible Flow ◽  
Turbulent Viscosity ◽  
Pressure Coefficient ◽  
Angle Of Attack ◽  
Extreme Condition ◽  
Bottom Surface ◽  
Shock Propagation ◽  
Nrel Phase Vi

The work is focused on numeric analysis of compressible flow around National Renewable Energy Laboratory (NREL) phase VI wind turbine blade airfoil S809. Although wind turbine airfoils are low Reynolds number airfoils, a reasonable investigation of compressible flow under extreme condition might be helpful. A subsonic flow (mach no.M=0.8) has been considered for this analysis and the impacts of this flow under seven different angles of attack have been determined. The results show that shock takes place just after the mid span at the top surface and just before the mid span at the bottom surface at zero angle of attack. Slowly the shock waves translate their positions as angle of attack increases. A relative translation of the shock waves in upper and lower face of the airfoil are presented. Variation of Turbulent viscosity ratio and surface Y+ have also been determined. Ak-ωSST turbulent model is considered and the commercial CFD code ANSYS FLUENT is used to find the pressure coefficient (Cp) as well as the lift (CL) and drag coefficients (CD). A graphical comparison of shock propagation has been shown with different angle of attack. Flow separation and stream function are also determined.

scholarly journals Controlling dynamic stall using vortex generators on a wind turbine airfoil

2021 ◽  
Author(s):  
D. De Tavernier ◽  
C. Ferreira ◽  
A. Viré ◽  
B. LeBlanc ◽  
S. Bernardy
Keyword(s):  
Wind Turbine ◽  
Vortex Generators ◽  
Dynamic Stall ◽  
Wind Turbine Airfoil

scholarly journals Closed loop control of aerodynamic load fluctuations on wind turbine airfoil using surface plasma actuators

2020 ◽  
Vol 53 (2) ◽  
pp. 12675-12681
Author(s):  
Dominique Nelson-Gruel ◽  
Pierrick Joseph ◽  
Alexis Paulh-Manssens ◽  
Annie Leroy ◽  
Sandrine Aubrun ◽  
...  
Keyword(s):  
Wind Turbine ◽  
Closed Loop ◽  
Plasma Actuators ◽  
Aerodynamic Load ◽  
Closed Loop Control ◽  
Surface Plasma ◽  
Loop Control ◽  
Wind Turbine Airfoil

Three-Dimensional and Rotational Aerodynamics on the NREL Phase VI Wind Turbine Blade

2008 ◽  
Vol 130 (3) ◽  
Author(s):  
Alvaro Gonzalez ◽  
Xabier Munduate
Keyword(s):  
Wind Turbine ◽  
Turbine Blade ◽  
Three Dimensional ◽  
Separated Flow ◽  
Leading Edge ◽  
Wind Turbine Blade ◽  
Trailing Edge ◽  
Rotating Blade ◽  
Nrel Phase Vi ◽  
Edge Separation

This work undertakes an aerodynamic analysis over the parked and the rotating NREL Phase VI wind turbine blade. The experimental sequences from NASA Ames wind tunnel selected for this study respond to the parked blade and the rotating configuration, both for the upwind, two-bladed wind turbine operating at nonyawed conditions. The objective is to bring some light into the nature of the flow field and especially the type of stall behavior observed when 2D aerofoil steady measurements are compared to the parked blade and the latter to the rotating one. From averaged pressure coefficients together with their standard deviation values, trailing and leading edge separated flow regions have been found, with the limitations of the repeatability of the flow encountered on the blade. Results for the parked blade show the progressive delay from tip to root of the trailing edge separation process, with respect to the 2D profile, and also reveal a local region of leading edge separated flow or bubble at the inner, 30% and 47% of the blade. For the rotating blade, results at inboard 30% and 47% stations show a dramatic suppression of the trailing edge separation, and the development of a leading edge separation structure connected with the extra lift.

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