Two-dimensional wind tunnel tests of the SSS series 1 structurally efficient aerofoils for wind turbines
Two-dimensional wind tunnel tests of the SSS series 1 structurally efficient aerofoils for wind turbines
The two-dimensional lift, drag, and quarter chord moment coefficients were measured for the new design Southampton Ship Science series 1 aerofoils for angles of attack between a minimum of - 6° and a maximum of 21°. Five of the new series aerofoils were tested with thickness-chord ratio varying in 2% increments between 21% and 29%. An LS(1) 0421 mod aerofoil was also tested. All six aerofoils had a 610mm chord and an overall span of 995mm.
The aerofoils were tested over a three week period using a two-dimensional test rig designed for use in the Southampton University 11' * 8' working section closed return low speed wind tunnel. A detailed description of the design, operation and installation of this test rig forms the main part of this report.
The aerodynamic forces and moments were measured on the central 595mm span of the aerofoil using two three-component strain gauge balances. A wake traverse mechanism 0.5 chord downstream of the aerofoil trailing edge was used to obtain a further drag measurement.
Results for each aerofoil are presented in the form of Lift-Incidence, Drag-Lift, and Moment-Lift polars. Tests were conducted at a chord Reynolds number of 1600000 and 2000000. Measurements with a roughness strip applied at 5% chord from the leading edge were also obtained.
University of Southampton
Turnock, S.R.
d6442f5c-d9af-4fdb-8406-7c79a92b26ce
1989
Turnock, S.R.
d6442f5c-d9af-4fdb-8406-7c79a92b26ce
Turnock, S.R.
(1989)
Two-dimensional wind tunnel tests of the SSS series 1 structurally efficient aerofoils for wind turbines
(Ship Science Reports, 38)
Southampton, UK.
University of Southampton
138pp.
Record type:
Monograph
(Project Report)
Abstract
The two-dimensional lift, drag, and quarter chord moment coefficients were measured for the new design Southampton Ship Science series 1 aerofoils for angles of attack between a minimum of - 6° and a maximum of 21°. Five of the new series aerofoils were tested with thickness-chord ratio varying in 2% increments between 21% and 29%. An LS(1) 0421 mod aerofoil was also tested. All six aerofoils had a 610mm chord and an overall span of 995mm.
The aerofoils were tested over a three week period using a two-dimensional test rig designed for use in the Southampton University 11' * 8' working section closed return low speed wind tunnel. A detailed description of the design, operation and installation of this test rig forms the main part of this report.
The aerodynamic forces and moments were measured on the central 595mm span of the aerofoil using two three-component strain gauge balances. A wake traverse mechanism 0.5 chord downstream of the aerofoil trailing edge was used to obtain a further drag measurement.
Results for each aerofoil are presented in the form of Lift-Incidence, Drag-Lift, and Moment-Lift polars. Tests were conducted at a chord Reynolds number of 1600000 and 2000000. Measurements with a roughness strip applied at 5% chord from the leading edge were also obtained.
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Published date: 1989
Additional Information:
ISSN 0140-3818
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Local EPrints ID: 43724
URI: http://eprints.soton.ac.uk/id/eprint/43724
PURE UUID: c3542140-e124-45c0-9674-df874885db2b
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Date deposited: 30 Jan 2007
Last modified: 16 Mar 2024 02:37
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