An experimental investigation on tapered wings with leading-edge protuberances

Particle Image Velocimetry (PIV) experiments were conducted in a water tunnel to study vortex interactions around tapered swept wings with leading edge tubercles. Two airfoil models based on the SD7032 airfoil profile were tested at Reynolds number 9100 and angles of attack (α) of -10°,10° and 25°,...

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Main Author: Ee, Marcus Joon Leng
Other Authors: New Tze How, Daniel
Format: Final Year Project
Language:English
Published: Nanyang Technological University 2023
Subjects:
Online Access:https://hdl.handle.net/10356/168370
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Institution: Nanyang Technological University
Language: English
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spelling sg-ntu-dr.10356-1683702023-06-17T16:51:50Z An experimental investigation on tapered wings with leading-edge protuberances Ee, Marcus Joon Leng New Tze How, Daniel School of Mechanical and Aerospace Engineering DTHNEW@ntu.edu.sg Engineering::Aeronautical engineering::Aerodynamics Engineering::Aeronautical engineering::Aircraft Particle Image Velocimetry (PIV) experiments were conducted in a water tunnel to study vortex interactions around tapered swept wings with leading edge tubercles. Two airfoil models based on the SD7032 airfoil profile were tested at Reynolds number 9100 and angles of attack (α) of -10°,10° and 25°, with the latter two representing the pre-stall and post-stall regimes respectively. Flow visualisation was also performed on airfoils at negative angles of attack for the first time. Results at positive angles of attack show that the baseline wing experiences significant flow separation at the outboard region while flow remains attached at the inboard region. Leading edge tubercles are shown to provide effective flow control by maintaining flow attachment and mitigating shear layer formation at high angles of attack even at the outboard region of the wing. At higher pitch angles, flow also reattaches along the tubercle peaks while most of flow along the baseline wing remains separated. Flow visualisation at negative angle of attack shows high vorticity along the pressure surface of both wings. Vorticity of the tubercled wing was noticeably worse than that of the baseline wing, suggesting a negative effect of tubercle curvature on flow stability at negative angles of attack. Bachelor of Engineering (Aerospace Engineering) 2023-06-12T04:23:49Z 2023-06-12T04:23:49Z 2023 Final Year Project (FYP) Ee, M. J. L. (2023). An experimental investigation on tapered wings with leading-edge protuberances. Final Year Project (FYP), Nanyang Technological University, Singapore. https://hdl.handle.net/10356/168370 https://hdl.handle.net/10356/168370 en B177 application/pdf Nanyang Technological University
institution Nanyang Technological University
building NTU Library
continent Asia
country Singapore
Singapore
content_provider NTU Library
collection DR-NTU
language English
topic Engineering::Aeronautical engineering::Aerodynamics
Engineering::Aeronautical engineering::Aircraft
spellingShingle Engineering::Aeronautical engineering::Aerodynamics
Engineering::Aeronautical engineering::Aircraft
Ee, Marcus Joon Leng
An experimental investigation on tapered wings with leading-edge protuberances
description Particle Image Velocimetry (PIV) experiments were conducted in a water tunnel to study vortex interactions around tapered swept wings with leading edge tubercles. Two airfoil models based on the SD7032 airfoil profile were tested at Reynolds number 9100 and angles of attack (α) of -10°,10° and 25°, with the latter two representing the pre-stall and post-stall regimes respectively. Flow visualisation was also performed on airfoils at negative angles of attack for the first time. Results at positive angles of attack show that the baseline wing experiences significant flow separation at the outboard region while flow remains attached at the inboard region. Leading edge tubercles are shown to provide effective flow control by maintaining flow attachment and mitigating shear layer formation at high angles of attack even at the outboard region of the wing. At higher pitch angles, flow also reattaches along the tubercle peaks while most of flow along the baseline wing remains separated. Flow visualisation at negative angle of attack shows high vorticity along the pressure surface of both wings. Vorticity of the tubercled wing was noticeably worse than that of the baseline wing, suggesting a negative effect of tubercle curvature on flow stability at negative angles of attack.
author2 New Tze How, Daniel
author_facet New Tze How, Daniel
Ee, Marcus Joon Leng
format Final Year Project
author Ee, Marcus Joon Leng
author_sort Ee, Marcus Joon Leng
title An experimental investigation on tapered wings with leading-edge protuberances
title_short An experimental investigation on tapered wings with leading-edge protuberances
title_full An experimental investigation on tapered wings with leading-edge protuberances
title_fullStr An experimental investigation on tapered wings with leading-edge protuberances
title_full_unstemmed An experimental investigation on tapered wings with leading-edge protuberances
title_sort experimental investigation on tapered wings with leading-edge protuberances
publisher Nanyang Technological University
publishDate 2023
url https://hdl.handle.net/10356/168370
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