Experimental and Numerical Study of the Effect of Varying Sinusoidal Bumps Height at the Leading Edge of the NASA LS (1)-0413 Airfoil at Low Reynolds Number

Authors

  • Bashir Isyaku Kunya Department of Mechanical Engineering, Kano University of Science and Technology, Wudil, Nigeria
  • Clement O. Folayan Department of Mechanical Engineering, Ahmadu Bello University, Zaria, Nigeria
  • Gyang Yakubu Pam Department of Mechanical Engineering, Ahmadu Bello University, Zaria, Nigeria
  • Fatai Olukayode Anafi Department of Mechanical Engineering, Ahmadu Bello University, Zaria, Nigeria
  • Nura Muaz Muhammad Department of Mechanical Engineering, Kano University of Science and Technology, Wudil, Nigeria

Keywords:

angle of attack, lift coefficient, drag coefficient, bumps height, Reynolds number

Abstract

This research work is about numerical simulation and experimental study of the effect of varying sinusoidal bumps (or tubercles) height at the leading edge of the airfoil on efficiency using NASA LS (1)-0413 cross-section profiles. Spalart Allmaras turbulence model was used for numerical solutions. The parameters investigated include, lift, and drag, the angle of attack and bumps height at very low Reynolds number of 4.9 x 104. The results show that bumps on the blade leading edge have an advantage at post-stall angles of attack on the performance and varies with bumps height.

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Published

2021-07-05

Issue

Vol. 11 No. 3: CFD Letters,March (2019)

Section

Articles
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