Turbulent subsonic flow over swept airfoils with blunt trailing edges will be studied in three major phases. First, techniques for attenuating vortex shedding from two-dimensional blunt bodies will be studied and the results applied to three-dimensional bodies. In the next phase, methods for controlling spanwise vortical flow associated with separated-flow regions downstream of swept rearward-facing steps and near the trailing edges of swept lifting airfoils will be investigated. The third phase applies the results of the first two phases to the design of swept lifting airfoils with blunt trailing edges which incur no drag penalty for the bluntness.
