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Aerodynamics of harmonically oscillating aerofoil at low Reynolds number

Two-dimensional flows over harmonically oscillating symmetrical aerofoil at reduced frequency of 0.1 were investigated for a Reynolds number of 135,000, with focus on the unsteady aerodynamic forces, pressure and vortex dynamics at post-stall angles of attack. Numerical simulations using ANSYS® FLUE...

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Main Authors: Rahman, A. H. A., Mohd, N. A. R. N., Lazim, T. M., Mansor, S.
Format: Article
Language:English
Published: Journal of Aerospace Technology and Management 2017
Subjects:
TJ Mechanical engineering and machinery
Online Access:http://eprints.utm.my/id/eprint/76404/1/LazimTM2017_AerodynamicsofHarmonicallyOscillatingAerofoil.pdf
http://eprints.utm.my/id/eprint/76404/
https://www.scopus.com/inward/record.uri?eid=2-s2.0-85014656063&doi=10.5028%2fjatm.v9i1.610&partnerID=40&md5=dda7e65eb1231081eddca5001bfcf06a
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spelling my.utm.764042018-04-30T13:26:10Z http://eprints.utm.my/id/eprint/76404/ Aerodynamics of harmonically oscillating aerofoil at low Reynolds number Rahman, A. H. A. Mohd, N. A. R. N. Lazim, T. M. Mansor, S. TJ Mechanical engineering and machinery Two-dimensional flows over harmonically oscillating symmetrical aerofoil at reduced frequency of 0.1 were investigated for a Reynolds number of 135,000, with focus on the unsteady aerodynamic forces, pressure and vortex dynamics at post-stall angles of attack. Numerical simulations using ANSYS® FLUENT CFD solver, validated by wind tunnel experiment, were performed to study the method of sliding mesh employed to control the wing oscillation. The transport of flow was solved using incompressible, unsteady Reynolds-Averaged Navier-Stokes equations. The 2-equation k-ε realizable turbulence model was used as turbulence closure. At large angle of attack, complex flows structure developed on the upper surface of the aerofoil induced vortex shedding from the activity of separated flows and interaction of the leading edge vortex with the trailing edge one. This interaction at some stage promotes the generation of lift force and delays the static stall. In this investigation, it was found that the sliding mesh method combined with the k-ε realizable turbulence model provides better aerodynamic loads predictions compared to the methods reported in literature. Journal of Aerospace Technology and Management 2017 Article PeerReviewed application/pdf en http://eprints.utm.my/id/eprint/76404/1/LazimTM2017_AerodynamicsofHarmonicallyOscillatingAerofoil.pdf Rahman, A. H. A. and Mohd, N. A. R. N. and Lazim, T. M. and Mansor, S. (2017) Aerodynamics of harmonically oscillating aerofoil at low Reynolds number. Journal of Aerospace Technology and Management, 9 (1). pp. 83-90. ISSN 1984-9648 https://www.scopus.com/inward/record.uri?eid=2-s2.0-85014656063&doi=10.5028%2fjatm.v9i1.610&partnerID=40&md5=dda7e65eb1231081eddca5001bfcf06a DOI:10.5028/jatm.v9i1.610
institution Universiti Teknologi Malaysia
building UTM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Malaysia
content_source UTM Institutional Repository
url_provider http://eprints.utm.my/
language English
topic TJ Mechanical engineering and machinery
spellingShingle TJ Mechanical engineering and machinery
Rahman, A. H. A.
Mohd, N. A. R. N.
Lazim, T. M.
Mansor, S.
Aerodynamics of harmonically oscillating aerofoil at low Reynolds number
description Two-dimensional flows over harmonically oscillating symmetrical aerofoil at reduced frequency of 0.1 were investigated for a Reynolds number of 135,000, with focus on the unsteady aerodynamic forces, pressure and vortex dynamics at post-stall angles of attack. Numerical simulations using ANSYS® FLUENT CFD solver, validated by wind tunnel experiment, were performed to study the method of sliding mesh employed to control the wing oscillation. The transport of flow was solved using incompressible, unsteady Reynolds-Averaged Navier-Stokes equations. The 2-equation k-ε realizable turbulence model was used as turbulence closure. At large angle of attack, complex flows structure developed on the upper surface of the aerofoil induced vortex shedding from the activity of separated flows and interaction of the leading edge vortex with the trailing edge one. This interaction at some stage promotes the generation of lift force and delays the static stall. In this investigation, it was found that the sliding mesh method combined with the k-ε realizable turbulence model provides better aerodynamic loads predictions compared to the methods reported in literature.
format Article
author Rahman, A. H. A.
Mohd, N. A. R. N.
Lazim, T. M.
Mansor, S.
author_facet Rahman, A. H. A.
Mohd, N. A. R. N.
Lazim, T. M.
Mansor, S.
author_sort Rahman, A. H. A.
title Aerodynamics of harmonically oscillating aerofoil at low Reynolds number
title_short Aerodynamics of harmonically oscillating aerofoil at low Reynolds number
title_full Aerodynamics of harmonically oscillating aerofoil at low Reynolds number
title_fullStr Aerodynamics of harmonically oscillating aerofoil at low Reynolds number
title_full_unstemmed Aerodynamics of harmonically oscillating aerofoil at low Reynolds number
title_sort aerodynamics of harmonically oscillating aerofoil at low reynolds number
publisher Journal of Aerospace Technology and Management
publishDate 2017
url http://eprints.utm.my/id/eprint/76404/1/LazimTM2017_AerodynamicsofHarmonicallyOscillatingAerofoil.pdf
http://eprints.utm.my/id/eprint/76404/
https://www.scopus.com/inward/record.uri?eid=2-s2.0-85014656063&doi=10.5028%2fjatm.v9i1.610&partnerID=40&md5=dda7e65eb1231081eddca5001bfcf06a
_version_ 1643657301074116608
score 13.211869

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