The Design and Low Mach Number Wind-Tunnel Performance of a Modified NACA 23012 Aerofoil, With an Investigation of Dynamic Stall Onset

[摘要] In recent years, much of the research into aerodynamics performed at the University of Glasgow has considered the behaviour of helicopter and wind-turbine aerofoils in unsteady conditions. Theoretical predictive algorithms have not yet been developed fully and so there is still a great need to examine experimentally-recorded data. The present research was undertaken in an attempt to increase knowledge of the mechanism of trailing-edge dynamic stall at low Mach numbers. Consequently, the NACA 23012 aerofoil section has been modified over the trailing 75% chord to increase camber, and a model of the resulting aerofoil subjected to a series of wind-tunnel experiments.

[发布机构] University:University of Glasgow

[关键词] Aerospace engineering