Abstract
Abstract : In an effort to determine the impact of various wing parameters on the abrupt wing stall phenomenon encountered by the pre-production F/A-18E, various characteristics of the F/A-18C wing were modified to reflect the design changes incorporated into the F/A-18E wing. The parameters evaluated during this study included thickness, camber, twist, leading-edge radius, leading-edge flap-chord ratio and the addition of a leading-edge snag. The wing parameters were modified independently and then in combination to determine their impact on the abrupt stall. Several potential computational Figures of Merit were evaluated to determine their utility for the prediction of an abrupt wing stall. One of the most promising Figures of Merit for indicating the onset of an abrupt stall was found to be the wingroot bending-moment coefficient. Using this Figure of Merit, it was determined that the incorporation of a leading-edge snag, the reduction of leading-edge flap-chord ratio and the elimination of camber are the likely contributors to the abrupt stall phenomenon encountered by the aircraft.
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