Evaluation of Streamline on Aerofoil with Suction Hole in Wind Tunnel

Authors

  • Basnayake Mudiyanselage Sachinthana Bandara Moonamale Faculty of Mechanical Engineering, Universiti Teknologi Malaysia 81310 UTM Johor Bahru Johor, Malaysia
  • Syahrullail Samion Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 UTM Johor Bahru, Johor, Malaysia
  • Mohamad Nor Musa Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 UTM Johor Bahru, Johor, Malaysia
  • Kamyar Shameli Institute of Virology, Department of Medicine, Technical University of Munich, Munich, 81675, Germany
  • M’hamed Beriache Rheology and Mechanics Laboratory, Faculty of Technology, Department of Mechanical Engineering, University Hassiba Benbouali, Algeria

DOI:

https://doi.org/10.37934/arefmht.13.1.17

Keywords:

pressure suction slot, NACA0012, wind tunnel, aerofoil analysis

Abstract

This study looks into the impact of pressure suction holes in the NACA 0012 airfoil on aerodynamic performance. The goal is to use wind tunnel tests to compute the lift and drag forces for the NACA 0012 airfoil with suction holes at various air speeds and angles of attack. The relationship between air speed, angle of attack, drag coefficient, and lift coefficient will be determined by analysing the obtained data. The goal of the research is to better understand the flow patterns and variations in streamlines of the NACA 0012 airfoil at different velocity and attack angles. The test model will use the NACA 0012 airfoil, which is recognised for its symmetrical shape. Suction holes, varying from one to four, will be installed to provide insight into the influence of pressure suction on the boundary layer and streamline behaviour of the airfoil. The study will be carried out in a low-speed wind tunnel within the Fluid Mechanics laboratory, with the streamlines visualised using a smoke generator. This study is significant because it contributes to our understanding of flow characteristics, pressure distributions, and boundary layer control in aerodynamic design. It also provides excellent exposure to wind tunnel testing procedures, aviation industry practises, and continuing airfoil design research. This study adds to the body of knowledge on optimising airfoil performance by evaluating the effect of pressure suction holes on the NACA 0012 airfoil. The findings will be useful to researchers, aerodynamic enthusiasts, and aviation experts, allowing them to further investigate the potential benefits of pressure suction techniques in improving airfoil efficiency and performance.

Downloads

Download data is not yet available.

Author Biography

Syahrullail Samion, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 UTM Johor Bahru, Johor, Malaysia

syahruls@mail.fkm.utm.my

Downloads

Published

2024-03-07

How to Cite

Basnayake Mudiyanselage Sachinthana Bandara Moonamale, Syahrullail Samion, Mohamad Nor Musa, Kamyar Shameli, & M’hamed Beriache. (2024). Evaluation of Streamline on Aerofoil with Suction Hole in Wind Tunnel. Journal of Advanced Research in Experimental Fluid Mechanics and Heat Transfer, 13(1), 1–7. https://doi.org/10.37934/arefmht.13.1.17
سرور مجازی ایران Decentralized Exchange

Issue

Section

Articles
فروشگاه اینترنتی