A computational inverse procedure for transonic airfoils in which shapes are determined supporting prescribed pressure distributions, is presented. The method uses the small disturbance equation, and a consistent analysis-design differencing procedure at the airfoil surface. This avoids the intermediate analysis-design-analysis iterations. The effect of any openness at the trailing edge is taken into account by adding an effective source term into the far field. A systematic expansion procedure which models the far field for solid tunnel walls is presented along with some design results for the associated boundary conditions and those for a free field.(Buehn)
Computational transonic airfoil design in free air and a wind tunnel
Die numerische Berechnung eines transsonischen Tragfluegelentwurfs in freier Umstroemung und im Windkanal
AIAA-Papers ; 1-8
1978
8 Seiten, 9 Bilder, 11 Quellen
Conference paper
English
AIAA | 1971
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