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

Bashir Isyaku  Kunya; Clement  O. Folayan; Gyang  Yakubu Pam; Fatai Olukayode  Anafi; Nura Muaz  Muhammad

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

2021-01-16

How to Cite

Kunya, B. I. ., O. Folayan, C. ., Yakubu Pam, G. ., Anafi, F. O. ., & Muhammad, N. M. . (2021). 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. CFD Letters, 11(3), 129–144. Retrieved from https://akademiabaru.com/submit/index.php/cfdl/article/view/3149