Design approach with wind tunnel test data on an RPV laboratory for in-flight aerofoil testing

Darida, Mauro (1998) Design approach with wind tunnel test data on an RPV laboratory for in-flight aerofoil testing. UNSPECIFIED thesis, University of Glasgow.

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Abstract

Presently wind tunnels are deployed to collect the majority of the experimental data on aerofoils and on boundary layer investigations, but they have their own disadvantages. Flight testing, especially at higher Reynolds numbers, gives a practical solution to these disadvantages, but has a critical influence on the direct cost of experiments. A design study was carried out to modify an RPV, named "Condor", to demonstrate the potential use of an RPV system for in-flight laminar aerofoil research at a fraction of the cost on a manned aircraft. A wing glove, namely an outsized and removable aerofoil section attached to the wing of the RPV, was designed and built. A wind tunnel/numerical investigation was conducted to evaluate the resulting RPV wing/glove combination. Numerical modelling proved it to be capable of providing flowfield details that pointed out the need for endplates in order to acquire infinite wing aerofoil data over the glove surface. Wind tunnel testing included pressure measurements and surface flow visualization and was most beneficial in the endplates design and in validating the pressure sensing system for future flight testing. The investigation included an effort to measure the pressure distribution produced by simulated ice formations on the glove leading edge. General observations deducted from these results are presented.

Item Type: Thesis (UNSPECIFIED)
Qualification Level: Masters
Additional Information: Adviser: L Smrcek
Keywords: Aerospace engineering
Date of Award: 1998
Depositing User: Enlighten Team
Unique ID: glathesis:1998-71931
Copyright: Copyright of this thesis is held by the author.
Date Deposited: 17 May 2019 09:31
Last Modified: 20 May 2019 13:23
URI: http://theses.gla.ac.uk/id/eprint/71931

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