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Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets

Main Authors: Ghazali, M.I; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia. Universiti Kuala Lumpur MFI, 43650 Bandar Baru Bangi, Malaysia., Harun, Z.; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia, Wan Ghopa, W.A; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia., Abbas, A. A; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia.
Format: Article info application/pdf eJournal
Bahasa: eng
Terbitan: International Journal on Advanced Science, Engineering and Information Technology , 2016
Subjects:
airfoil
riblets
turbulent
drag
Online Access: http://insightsociety.org/ojaseit/index.php/ijaseit/article/view/901
http://insightsociety.org/ojaseit/index.php/ijaseit/article/view/901/pdf_214
ctrlnum article-901
fullrecord <?xml version="1.0"?> <dc schemaLocation="http://www.openarchives.org/OAI/2.0/oai_dc/ http://www.openarchives.org/OAI/2.0/oai_dc.xsd"><title lang="en-US">Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets</title><creator>Ghazali, M.I; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia. Universiti Kuala Lumpur MFI, 43650 Bandar Baru Bangi, Malaysia.</creator><creator>Harun, Z.; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia</creator><creator>Wan Ghopa, W.A; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia.</creator><creator>Abbas, A. A; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia.</creator><subject lang="en-US">airfoil; riblets; turbulent; drag</subject><description lang="en-US">The aims of this research is to look into the percentage drag reduction on a NACA 0026 airfoil with V-Groove riblets installed around at some locations around its surface. NACA 0026 is a symmetrical airfoil mostly used as turbine blade and aircraft wing. Research on drag reduction by using riblets on the surface was introduced by NASA Langley Research Centre in 1970s. There are many types of riblet designed in this research area such as V groove, segmented blade and continuous sawtooth. This research used NACA 0026 with external geometry 500 mm spans, 615 mm chord and 156 mm thickness. V-groove riblets with 1 mm pitch and 1 mm high and 30 mm width are attached at peak points of the airfoil profile. The CFD simulation used ANSYS Fluent to analyze the velocity, pressure gradient, turbulent kinetic energy and vortex development. The result shows the percentage in drag reduction compared to clean surface for the zero angle of attack is 11.8% and 300 angle of attack is 1.64%. By this condition the airfoil will have better motion performance in their applications.</description><publisher lang="en-US">International Journal on Advanced Science, Engineering and Information Technology</publisher><contributor lang="en-US"/><date>2016-08-08</date><type>Journal:Article</type><type>Other:info:eu-repo/semantics/publishedVersion</type><type>Other:</type><type>File:application/pdf</type><identifier>http://insightsociety.org/ojaseit/index.php/ijaseit/article/view/901</identifier><identifier>10.18517/ijaseit.6.4.901</identifier><source lang="en-US">International Journal on Advanced Science, Engineering and Information Technology; Vol 6, No 4 (2016); 529-533</source><source>2460-6952</source><source>2088-5334</source><language>eng</language><relation>http://insightsociety.org/ojaseit/index.php/ijaseit/article/view/901/pdf_214</relation><recordID>article-901</recordID></dc>
language eng
format Journal:Article
Journal
Other:info:eu-repo/semantics/publishedVersion
Other
Other:
File:application/pdf
File
Journal:eJournal
author Ghazali, M.I; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia. Universiti Kuala Lumpur MFI, 43650 Bandar Baru Bangi, Malaysia.
Harun, Z.; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia
Wan Ghopa, W.A; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia.
Abbas, A. A; Universiti Kebangsaan Malaysia, 43600 Bangi, Malaysia.
title Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets
publisher International Journal on Advanced Science, Engineering and Information Technology
publishDate 2016
topic airfoil
riblets
turbulent
drag
url http://insightsociety.org/ojaseit/index.php/ijaseit/article/view/901
http://insightsociety.org/ojaseit/index.php/ijaseit/article/view/901/pdf_214
contents The aims of this research is to look into the percentage drag reduction on a NACA 0026 airfoil with V-Groove riblets installed around at some locations around its surface. NACA 0026 is a symmetrical airfoil mostly used as turbine blade and aircraft wing. Research on drag reduction by using riblets on the surface was introduced by NASA Langley Research Centre in 1970s. There are many types of riblet designed in this research area such as V groove, segmented blade and continuous sawtooth. This research used NACA 0026 with external geometry 500 mm spans, 615 mm chord and 156 mm thickness. V-groove riblets with 1 mm pitch and 1 mm high and 30 mm width are attached at peak points of the airfoil profile. The CFD simulation used ANSYS Fluent to analyze the velocity, pressure gradient, turbulent kinetic energy and vortex development. The result shows the percentage in drag reduction compared to clean surface for the zero angle of attack is 11.8% and 300 angle of attack is 1.64%. By this condition the airfoil will have better motion performance in their applications.
id IOS1116.article-901
institution Indonesian Society for Knowledge and Human Development
institution_id 204
institution_type library:special
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library Indonesian Society for Knowledge and Human Development
library_id 78
collection International Journal on Advanced Science, Engineering and Information Technology
repository_id 1116
subject_area Program Komputer dan Teknologi Informasi
city -
province DKI JAKARTA
repoId IOS1116
first_indexed 2016-09-16T19:26:22Z
last_indexed 2016-09-16T19:26:36Z
recordtype dc
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