Design Procedure to Modify the Trailing Edge Upper Surface Pressure Gradient of a Given Aerofoil

摘要

A method whereby the pressure gradient on the trailing edge upper surface of a given airfoil may be modified to enhance or reduce trailing-edge separation during dynamic stall, for a given section, while retaining the leading edge pressure distribution, is outlined. The NACA 23012 airfoil was modified to enhance the boundary layer separation at the trailing-edge. The modification procedure consists of three algorithms: a potential flow panel method allowing calculation of the original pressure gradient at any angle of attack; a procedure allowing the modification of this gradient; and an inverse potential flow panel method to calculate a new profile from the modified vorticity distribution.