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

Gracey, Mark William (1991) The Design and Low Mach Number Wind-Tunnel Performance of a Modified NACA 23012 Aerofoil, With an Investigation of Dynamic Stall Onset. PhD thesis, University of Glasgow.

Abstract

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.

• Item Type: Thesis (PhD)
• Qualification Level: Doctoral
• Keywords: Aerospace engineering
• Date of Award: 1991
• Depositing User: Enlighten Team
• Unique ID: glathesis:1991-77275
• Copyright: Copyright of this thesis is held by the author.
• Date Deposited: 14 Jan 2020 09:13
• Last Modified: 14 Jan 2020 09:13
• URI: https://theses.gla.ac.uk/id/eprint/77275