Please use this identifier to cite or link to this item: https://hdl.handle.net/2440/103892
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Type: Journal article
Title: Performance effects of a single tubercle terminating at a swept wing’s tip
Author: Bolzon, M.
Kelso, R.
Arjomandi, M.
Citation: Experimental Thermal and Fluid Science, 2017; 85:52-68
Publisher: Elsevier
Issue Date: 2017
ISSN: 0894-1777
1879-2286
Statement of
Responsibility: 
Michael D. Bolzon, Richard M. Kelso, Maziar Arjomandi
Abstract: This study investigates the effects of a single tubercle terminating at a swept wing's tip on its performance at pre-stall angles of attack (AOAs). Two tubercle geometries with amplitudes of 10.5 mm and wavelengths of 60 mm were investigated. One geometry had a phase of π/2, which was termed the “peak” configuration, while the other had a phase of 3π/2, which was termed the “trough” configuration. Surface flow visualisation, force measurements, and wake surveys were conducted on the wing configurations at a 225,000 chord Reynolds number. The flow visualisation was conducted at 0°, 3°, 6°, 9°, and 12° AOAs, the wake surveys were conducted at 0°, 3°, 6°, and 9° AOAs, and the force measurements were conducted from −2° to 15° AOAs in 1° increments. The wings were NACA 0021 profiles, untapered, and swept at a 35° angle. Evidence of the flow mechanism “compartmentalization” was observed over the trough configuration at 12° AOA. At 1° and 2° AOAs, the tubercle configurations typically reduced the lift coefficient and lift-to-drag ratio by 3%, but neither configuration greatly affected the drag coefficient. Neither tubercle configuration greatly affected the lift coefficient, drag coefficient, or lift-to-drag ratio from 3° to 15° AOAs, with typical changes of 1% or 2% observed. Both tubercle configurations typically changed the induced and profile drag coefficients by 2% and 5%, respectively, from 0° to 9° AOAs. From 6° to 9° AOAs, the π/2 and 3π/2 tubercle configurations typically changed the wingtip vortex strength by 2.2%, and had opposite effects from each other.
Keywords: Leading edge tubercle; Flow control; Wake surveying; Wing performance
Description: Available online 16 February 2017
Rights: © 2017 Published by Elsevier Inc.
DOI: 10.1016/j.expthermflusci.2017.02.016
Published version: http://dx.doi.org/10.1016/j.expthermflusci.2017.02.016
Appears in Collections:Aurora harvest 7
Mechanical Engineering publications

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