Direct-Inverse Transonic Wing-Design Method in Curvilinear Coordinates Including Viscous Interaction

ABRIEF description of some developments in the directinverse wing design method is presented. The description includes a discussion of some observed spanwise oscillations and simple remedies, approximate limits on the wing planform, the significance of viscous interaction, and the feasibility of a design that begins aft of the leading edge and terminates prior to the trailing edge. Contents Many methods, ranging from optimization procedures to various inverse techniques, have been formulated using potential solvers to design wings in transonic flight. In the directinverse scheme,1 the desired pressure distribution, Cp, is numerically specified over all or part of the wing aft of the stagnation line via the wing's boundary condition. Flow tangency is enforced at the leading edge and in nondesign regions. The input Cp is tailored by an experienced engineer to weaken or eliminate shocks, to reduce excessively large adverse pressure gradients in the aft recovery region, and to provide reasonable pitching moments while maintaining an efficient