Numerical Aerodynamic Performance Evaluation of Airfoil with Protuberances on Leading Edge

• Main Authors: Hui-Ting Lin, 林惠婷
• Other Authors: Jen-Shiang Kouh
• Format: Others
• Language: zh-TW
• Published: 2011
• Online Access: http://ndltd.ncl.edu.tw/handle/61706441052363154703

碩士 === 國立臺灣大學 === 工程科學及海洋工程學研究所 === 99 === This study employs computational fluid dynamics (CFD) to investigate the effects of protuberances of varying geometric parameters on the performance of an airfoil with leading edge protuberances. The NACA 0012 airfoil is adopted as the baseline airfoil, and the geometric parameters are amplitude, wavelength, spanwise length, and number of protuberances.The results show that for an infinite wing, maximum lift coefficient increase with an increase in protuberance wavelength. For a finite wing, fixed aspect ratio, stall angle of attack, and stall lift coefficient all increase with the wavelength. As illustrated by flow visualizations, the leading edge protuberances generate vortices which impart kinetic energy to the boundary layer, such that the air remains attached to the suction surface of the wing, thereby maintaining laminar flow and avoiding turbulence. The kinetic energy from these vortices maintains or increases lift, and may be used to prevent stall by delaying separation.