Abstract
A computationall y efficient procedure for the design of shock-free supercritical wings is described. The method utilizes the fictitious-gas concept coupled with an improved version of the Jameson-Caughey fullpotential finite-difference code, FLO-22, for analyzing three-dimensional wings. The computation of the velocity components at the plane of symmetry in the analysis code is modified to simulate the flow on isolated wings more accurately. In addition, the improved version of FLO-22 is capable of handling the wing-fuselage interference effect. The present design method computes the surface geometry beneath the supersonic region so as to eliminate the shock waves normally associated with transonic flight. Results for redesigned rectangular and swept wings are presented that indicate significant wave-drag reduction and improved aerodynamic characteristics when compared with the baseline wing.
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