An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap

Flow control to suppress the boundary layer separation over the wmg can dramatically improve the performance of most aircraft in the take-off and lancling flight regime. Previous aerodynamic experiments and computations have indicated that unsteady excitation produced by the oscillating sub bound...

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Main Author:	Hussin, Fauzi
Format:	Thesis
Language:	English
Published:	2014
Subjects:	TK1-9971 Electrical engineering Electronics Nuclear engineering
Online Access:	http://eprints.usm.my/61101/1/24%20Pages%20from%2000001785045.pdf
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id	my-usm-ep.61101
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spelling	my-usm-ep.611012024-09-12T01:10:45Z An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap 2014-12 Hussin, Fauzi TK1-9971 Electrical engineering. Electronics. Nuclear engineering Flow control to suppress the boundary layer separation over the wmg can dramatically improve the performance of most aircraft in the take-off and lancling flight regime. Previous aerodynamic experiments and computations have indicated that unsteady excitation produced by the oscillating sub boundary layer vortex generators (SBVGs) can delay boundary layer separation and wing stall more effectively than steady flow perturbations generated by passive SBVGs. Preliminary aerodynamic experiments have been performed to evaluate the effects of both passive and oscillating SBVGs on the wing of Eagle 150B with a single slotted flap at deflection angle of 38°. Four sets of co rotating, delta shaped vane type SBVGs have been installed near to the leading edge of the flap. In addition, oscillating SBVGs were designed to oscillate in three different frequencies (0.5Hz, 1.2Hz and I. 7Hz). Baseline (No VGs), passive and oscillating SBVGs were tested at three different Reynolds numbers (Re=6.21 x lOS, Re=7.3xIOs and Re=8.4xIOs) and the aerodynamic characteristics were obtained using six-component balance instrument. For the baseline case (No VGs), its lift and drag characteristic at Reynolds number of 8.4x lOS and angle of attack of 26° varies with the theoretical data by 50% and 26.38%, respectively. 2014-12 Thesis http://eprints.usm.my/61101/ http://eprints.usm.my/61101/1/24%20Pages%20from%2000001785045.pdf application/pdf en public masters Perpustakaan Hamzah Sendut Pusat Pengajian Kejuruteraan Elektrik & Elektronik
institution	Universiti Sains Malaysia
collection	USM Institutional Repository
language	English
topic	TK1-9971 Electrical engineering Electronics Nuclear engineering
spellingShingle	TK1-9971 Electrical engineering Electronics Nuclear engineering Hussin, Fauzi An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap
description	Flow control to suppress the boundary layer separation over the wmg can dramatically improve the performance of most aircraft in the take-off and lancling flight regime. Previous aerodynamic experiments and computations have indicated that unsteady excitation produced by the oscillating sub boundary layer vortex generators (SBVGs) can delay boundary layer separation and wing stall more effectively than steady flow perturbations generated by passive SBVGs. Preliminary aerodynamic experiments have been performed to evaluate the effects of both passive and oscillating SBVGs on the wing of Eagle 150B with a single slotted flap at deflection angle of 38°. Four sets of co rotating, delta shaped vane type SBVGs have been installed near to the leading edge of the flap. In addition, oscillating SBVGs were designed to oscillate in three different frequencies (0.5Hz, 1.2Hz and I. 7Hz). Baseline (No VGs), passive and oscillating SBVGs were tested at three different Reynolds numbers (Re=6.21 x lOS, Re=7.3xIOs and Re=8.4xIOs) and the aerodynamic characteristics were obtained using six-component balance instrument. For the baseline case (No VGs), its lift and drag characteristic at Reynolds number of 8.4x lOS and angle of attack of 26° varies with the theoretical data by 50% and 26.38%, respectively.
format	Thesis
qualification_level	Master's degree
author	Hussin, Fauzi
author_facet	Hussin, Fauzi
author_sort	Hussin, Fauzi
title	An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap
title_short	An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap
title_full	An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap
title_fullStr	An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap
title_full_unstemmed	An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap
title_sort	experimental study of oscillating subboundary layer vortex generators application on a wing's flap
granting_institution	Perpustakaan Hamzah Sendut
granting_department	Pusat Pengajian Kejuruteraan Elektrik & Elektronik
publishDate	2014
url	http://eprints.usm.my/61101/1/24%20Pages%20from%2000001785045.pdf
_version_	1811772878733967360

An Experimental Study Of Oscillating Subboundary Layer Vortex Generators Application On A Wing'S Flap

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