High angle-of-attack aerodynamics of a straight wing with finite span using a discrete vortex method

Abstract

The leading-edge-suction-parameter modulated discrete vortex method is extended to a wing with a finite span and no sweep, in order to get the development of aerodynamic coefficients with an angle-of-attack, from attached to completely detached flow conditions. A first case considering the unsteady pitching motion of a flat plate is compared with published experimental and numerical results. Then, dependence of lift, drag, and pitching moment coefficients with the angle-of-attack is discussed for a wing built on an SD7003 airfoil at a constant angle-of-attack. The three-dimensional effects on the lift coefficient curve for a completely detached wing are established.