The study of the effect of the cavity on the flow over NACA 0012 and Selig 7003 aerofoil at Low Reynolds number using Vortex Shading Method

摘要

The primary goal of this paper is to study the effect of the cavity on the flow over the aerofoil at low Reynolds number using Vortex Shading method. At low Reynolds number Laminar Separation Bubble formation takes place. The paper aims to study the effect of Laminar Separation Bubble on the flow over the upper surface of the aerofoils and effect of cavities on the flow. The effect is studied by vortex shading method and coefficient of lift and drag is used as a monitor. The aerofoil selected for the study is NACA 0012 and Selig-Donovan 7003. Increase in coefficient of lift is observed in NACA 0012 aerofoil for a particular cavity parameter. The paper also addresses the practical application of cavities in aerofoils in correspondence to UAVs, MAVs and wind turbines that lie in the low Reynolds number flight regime.