Unsteady flow past a two-dimensional airfoil undergoing large-amplitude pitching motion
Journal
38th Aerospace Sciences Meeting and Exhibit
Date Issued
2000-12-01
Author(s)
Abstract
Unsteady flows past a two-dimensional NACA 0012 airfoil undergoing large-amplitude pitching motion has been investigated with a joint experimental and numerical study. The Reynolds number, Re, based on the airfoil chord and the reference incoming freestream velocity, ranged from 5000 to 15000. A pathline flow visualization was performed to provide global flow information as well as those for comparison. A hybrid vortex method was used to calculate the detailed flow quantities. In the present study, the associated vortex structure as well as aerodynamic forces are the primary concern. Analysis based on the forces contributed by fluid elements with nonvanishing vorticity has provided an insight of relationship between the aerodynamic forces and the evolution of dynamic stall vortices. This fact provides proper directions for flow manipulation regarding aerodynamic forces at high angle of attack. The effects of several parameters including the reduced frequency, κ and reduced amplitude, λ are also discussed in the present study. © 2000 by C.C.Chu et al.
Type
conference paper