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

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@article{IJASEIT901,
   author = {M.I Ghazali and Z. Harun and W.A Wan Ghopa and A. A Abbas},
   title = {Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets},
   journal = {International Journal on Advanced Science, Engineering and Information Technology},
   volume = {6},
   number = {4},
   year = {2016},
   pages = {529--533},
   keywords = {airfoil; riblets; turbulent; drag},
   abstract = {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.},
   issn = {2088-5334},
   publisher = {INSIGHT - Indonesian Society for Knowledge and Human Development},
   url = {http://ijaseit.insightsociety.org/index.php?option=com_content&view=article&id=9&Itemid=1&article_id=901},
   doi = {10.18517/ijaseit.6.4.901}
}

EndNote

%A Ghazali, M.I
%A Harun, Z.
%A Wan Ghopa, W.A
%A Abbas, A. A
%D 2016
%T Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets
%B 2016
%9 airfoil; riblets; turbulent; drag
%! Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets
%K airfoil; riblets; turbulent; drag
%X 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.
%U http://ijaseit.insightsociety.org/index.php?option=com_content&view=article&id=9&Itemid=1&article_id=901
%R doi:10.18517/ijaseit.6.4.901
%J International Journal on Advanced Science, Engineering and Information Technology
%V 6
%N 4
%@ 2088-5334

IEEE

M.I Ghazali,Z. Harun,W.A Wan Ghopa and A. A Abbas,"Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets," International Journal on Advanced Science, Engineering and Information Technology, vol. 6, no. 4, pp. 529-533, 2016. [Online]. Available: http://dx.doi.org/10.18517/ijaseit.6.4.901.

RefMan/ProCite (RIS)

TY  - JOUR
AU  - Ghazali, M.I
AU  - Harun, Z.
AU  - Wan Ghopa, W.A
AU  - Abbas, A. A
PY  - 2016
TI  - Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets
JF  - International Journal on Advanced Science, Engineering and Information Technology; Vol. 6 (2016) No. 4
Y2  - 2016
SP  - 529
EP  - 533
SN  - 2088-5334
PB  - INSIGHT - Indonesian Society for Knowledge and Human Development
KW  - airfoil; riblets; turbulent; drag
N2  - 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.
UR  - http://ijaseit.insightsociety.org/index.php?option=com_content&view=article&id=9&Itemid=1&article_id=901
DO  - 10.18517/ijaseit.6.4.901

RefWorks

RT Journal Article
ID 901
A1 Ghazali, M.I
A1 Harun, Z.
A1 Wan Ghopa, W.A
A1 Abbas, A. A
T1 Computational Fluid Dynamic Simulation on NACA 0026 Airfoil with V-Groove Riblets
JF International Journal on Advanced Science, Engineering and Information Technology
VO 6
IS 4
YR 2016
SP 529
OP 533
SN 2088-5334
PB INSIGHT - Indonesian Society for Knowledge and Human Development
K1 airfoil; riblets; turbulent; drag
AB 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.
LK http://ijaseit.insightsociety.org/index.php?option=com_content&view=article&id=9&Itemid=1&article_id=901
DO  - 10.18517/ijaseit.6.4.901