View in EDS PDF Full Text

Effect of Vortex Generators on NACA2412 Aerofoil at Different Angles of Attack for Aircraft Wings.

Saved in:
Bibliographic Details
Title: Effect of Vortex Generators on NACA2412 Aerofoil at Different Angles of Attack for Aircraft Wings.
Authors: Vignesh, R.1, Ashish, S.1, Sharma, Pranav L.1, Ganesan, Balaji1 gbalajihits@gmail.com, Ezhilmaran, G.2, Raja, Vijayanandh3, Sasikumar, S.4, Boopathy, G.5, Ganesan, Santhosh Kumar6
Source: International Journal of Vehicle Structures & Systems (IJVSS). 2026, Vol. 18 Issue 1, p113-118. 6p.
Subjects: Vortex generators, Angle of attack (Aerodynamics), Wind tunnel testing, Drag coefficient, Aerodynamics, Flow velocity, Aerofoils, Lift (Aerodynamics)
Abstract: Vortex generator and aerofoil geometry of the blade enhance the aerodynamic effectiveness of an aircraft wing. In this research work, a wind tunnel experiment was conducted to explore the impact of vortex generators on the aerodynamic characteristics of the NACA2412 airfoil. The primary goal of this study was to analyse the coefficients of lift, drag and CL/CD distributions across the NACA2412 airfoil blade at freestream velocities of 15m/s, 25m/s and 35m/s, utilizing a low-speed subsonic wind tunnel. In the wind tunnel, the impact of NACA2412 profile airfoils has been examined with the help of three component force balance instruments at various angles of attack such as 0°, 4°, 8°, 12° and 16° respectively and similarly in negative angle of attack of 0°, -4°, -8°, -12° and -16°. The target of the task is to find out the lift coefficient and drag coefficient at different vortex generator such as triangular vortex generator, gothic vortex generator and rectangular vortex generator and their different combination arranged over the wing of NACA2412 aerofoil at x/c of 0.25, 0.5 and 0.75. The results of the study showed that significant variations in the coefficients of lift, drag and CL/CD distributions across the airfoil blade at different freestream velocities and angles of attack. [ABSTRACT FROM AUTHOR]
Copyright of International Journal of Vehicle Structures & Systems (IJVSS) is the property of Carbon Magics Ltd and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
Description
Abstract:Vortex generator and aerofoil geometry of the blade enhance the aerodynamic effectiveness of an aircraft wing. In this research work, a wind tunnel experiment was conducted to explore the impact of vortex generators on the aerodynamic characteristics of the NACA2412 airfoil. The primary goal of this study was to analyse the coefficients of lift, drag and CL/CD distributions across the NACA2412 airfoil blade at freestream velocities of 15m/s, 25m/s and 35m/s, utilizing a low-speed subsonic wind tunnel. In the wind tunnel, the impact of NACA2412 profile airfoils has been examined with the help of three component force balance instruments at various angles of attack such as 0°, 4°, 8°, 12° and 16° respectively and similarly in negative angle of attack of 0°, -4°, -8°, -12° and -16°. The target of the task is to find out the lift coefficient and drag coefficient at different vortex generator such as triangular vortex generator, gothic vortex generator and rectangular vortex generator and their different combination arranged over the wing of NACA2412 aerofoil at x/c of 0.25, 0.5 and 0.75. The results of the study showed that significant variations in the coefficients of lift, drag and CL/CD distributions across the airfoil blade at different freestream velocities and angles of attack. [ABSTRACT FROM AUTHOR]
ISSN:09753060
DOI:10.4273/ijvss.18.1.21