TY - JOUR
T1 - Effects of leading-edge rod on dynamic stall performance of a wind turbine airfoil
AU - Zhong, Junwei
AU - Li, Jingyin
AU - Guo, Penghua
N1 - Publisher Copyright:
© 2017, © IMechE 2017.
PY - 2017/12/1
Y1 - 2017/12/1
N2 - A cylindrical rod placed at the leading edge of the S809 airfoil is used as an alternative for the conventional vortex generators. In this paper, extensive numerical investigations have been conducted on the effects of the rod on the static and dynamic stall performance of the S809 airfoil. The flows around the stationary and sinusoidally oscillating S809 airfoils at Re = 106 are simulated by solving the unsteady two-dimensional Reynolds-averaged Navier–Stokes equations with the Shear Stress Transport k–ω model. For the stationary airfoil, the leading edge rod can effectively enhance the aerodynamic characteristics of the airfoil and delay the stall angle, with the maximum lift–drag ratio increased by 30.7%. For the airfoil undergoing deep dynamic stall, the rod shows the capacity of eliminating the dynamic stall vortex at the leading edge and suppressing the flow separation at the tailing edge. It also reduces the peak of the negative pitching moment and the hysteresis effects substantially, and eliminates the negative damping sub-loop of the moment coefficient. Moreover, the distance between the rod and the airfoil has a strong influence on the lift forces but little effect on drag and moment coefficients of airfoil under deep dynamic stall.
AB - A cylindrical rod placed at the leading edge of the S809 airfoil is used as an alternative for the conventional vortex generators. In this paper, extensive numerical investigations have been conducted on the effects of the rod on the static and dynamic stall performance of the S809 airfoil. The flows around the stationary and sinusoidally oscillating S809 airfoils at Re = 106 are simulated by solving the unsteady two-dimensional Reynolds-averaged Navier–Stokes equations with the Shear Stress Transport k–ω model. For the stationary airfoil, the leading edge rod can effectively enhance the aerodynamic characteristics of the airfoil and delay the stall angle, with the maximum lift–drag ratio increased by 30.7%. For the airfoil undergoing deep dynamic stall, the rod shows the capacity of eliminating the dynamic stall vortex at the leading edge and suppressing the flow separation at the tailing edge. It also reduces the peak of the negative pitching moment and the hysteresis effects substantially, and eliminates the negative damping sub-loop of the moment coefficient. Moreover, the distance between the rod and the airfoil has a strong influence on the lift forces but little effect on drag and moment coefficients of airfoil under deep dynamic stall.
KW - Dynamic stall control
KW - S809 airfoil
KW - aerodynamic
KW - leading-edge rod
KW - numerical simulation
UR - https://www.scopus.com/pages/publications/85037547706
U2 - 10.1177/0957650917718453
DO - 10.1177/0957650917718453
M3 - 文章
AN - SCOPUS:85037547706
SN - 0957-6509
VL - 231
SP - 753
EP - 769
JO - Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy
JF - Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy
IS - 8
ER -