Abstract
An airfoil design method based on optimization procedures in computational aerodynamics is presented. This article extends the method to include subcritical compressible flow and a modified Stratford recovery distribution to alleviate the hard stall that is typical of Stratford-typ e airfoils. A procedure for optimizing the drag is also presented based on the Squire-Young drag formula. The performance characteristics of this airfoil are then tested with a compressible panel method and boundary-layer solver. The procedures for both incompressible and compressible flow have generated airfoils which generate more lift and less drag than other comparable airfoils. High-lift airfoils which display a smooth stall region have also been developed which hold promise for general aviation use. In addition, these airfoils offer the potential of improved performance in applications such as high-endurance aircraft, propellers, fans, and windmill blades where high lift-to-drag ratios are desired. A specific example of an airfoil designed for a wind turbine is presented and compared to an existing airfoil.
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