Numerical Investigation of Subsonic Flow Past a Flat Plate Aerofoil

Abstract

The present work numerically investigates the effect of two different trailing edge geometries such as sharp as well as blunt on the aerodynamic characteristics of a flat plate aerofoil. The modifications in the flow as well as aerodynamic characteristics of sharp and blunted trailing edge configurations of a flat plate aerofoil are systematically compared using pressure coefficient, lift coefficient, vortex shedding, etc. The study was conducted for a chord-wise Reynolds number of 4.99 × 105 at an angle of attack of 25°. The large difference in the pressure coefficient observed between the top and bottom surface in the case of blunt trailing edge as compared to sharp ones indicates that the blunted trailing edge geometry generates higher lift than the sharp trailing edge ones. It is observed from spectra that the vortex shedding for both the blunted and sharp trailing edge geometries occurs at a Strouhal number of around 0.34. The increase of energy as well as broader wake in the blunted trailing edge geometry indicates higher drag as compared to the sharp trailing edge geometry. Thus, this paper sufficiently demonstrates the effect of sharp and blunted trailing edge geometries on the aerodynamic characteristics of a flat plate aerofoil.