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.

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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: http://theses.gla.ac.uk/id/eprint/77275

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