AERODYNAMICS OF MANEUVERING SLENDER WINGS WITH LEADING-EDGE SEPARATION

A nonlinear theoretical technique is presented for treating the unstea dy aerodynamics of low-aspect-ratio wings with leading-edge separation in incompressible flow. Cases are treated for wings in steady flight and for those undergoing severe unsteady maneuver. The treatment exten ds classical slender wing theory to allow for large-scale motion along with possibly asymmetric wake development. Calculated results are pre sented for a variety of cases and are compared with related analyses a nd experiments. Examples studied include wings of delta and clipped-de lta planform. Flight conditions and maneuvers treated included sidesli p, sudden plunge, and rapid constant-rate roll at zero angle of attack . New results are interpreted in the light of wake history effects, a framework which provides a simplified means of interpreting the aerody namic response in the severe maneuver case. The ability of the calcula tions to reproduce observed phenomena under a wide variety of conditio ns supports the practical usefulness of the extended slender wing trea tment as a tool for gaining increased insight into the unsteady intera ction between low-aspect-ratio wings and their wakes.