Computational fluid dynamic simulation on NACA 0026 airfoil with V-groove riblets

M. I. Ghazali, Zambri Harun, Wan Aizon Wan Ghopa, A. A. Abbas

Research output: Contribution to journalArticle

2 Citations (Scopus)

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 saw tooth. 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 30° angle of attack is 1.64%. By this condition the airfoil will have better motion performance in their applications.

Original languageEnglish
Pages (from-to)529-533
Number of pages5
JournalInternational Journal on Advanced Science, Engineering and Information Technology
Volume6
Issue number4
DOIs
Publication statusPublished - 2016

Fingerprint

Hydrodynamics
Airfoils
Computational fluid dynamics
fluid mechanics
Drag reduction
Computer simulation
Research
Angle of attack
United States National Aeronautics and Space Administration
turbines
aircraft
Aircraft
Pressure gradient
Kinetic energy
Turbomachine blades
NASA
Tooth
teeth
Vortex flow
Turbines

Keywords

  • Airfoil
  • Drag
  • Riblets
  • Turbulent

ASJC Scopus subject areas

  • Agricultural and Biological Sciences(all)
  • Computer Science(all)
  • Engineering(all)

Cite this

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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 saw tooth. 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 30° angle of attack is 1.64{\%}. By this condition the airfoil will have better motion performance in their applications.",
keywords = "Airfoil, Drag, Riblets, Turbulent",
author = "Ghazali, {M. I.} and Zambri Harun and {Wan Ghopa}, {Wan Aizon} and Abbas, {A. A.}",
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AU - Harun, Zambri

AU - Wan Ghopa, Wan Aizon

AU - Abbas, A. A.

PY - 2016

Y1 - 2016

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 saw tooth. 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 30° angle of attack is 1.64%. By this condition the airfoil will have better motion performance in their applications.

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 saw tooth. 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 30° angle of attack is 1.64%. By this condition the airfoil will have better motion performance in their applications.

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