A Method for Predicting the Drag of Airfoils

A new approach is proposed to introduce a change in the physical model of the vorticity on the surface of airfoils which will provide a technique for determining the drag of an infinite span wing throughout the angle of attack range. This approach could provide a method for developing and/or selecting airfoils with lower drag at higher angles of attack to obtain better aircraft maneuver and climb capabilities and can be used to extrapolate small scale wind tunnel tests results accurately to higher Reynolds numbers. In addition, further studies could provide insight into the development of boundary layer control techniques for reducing wing drag.