Potential theory of the pressure distribution on a wing section shall always give the values bigger than the ones obtained from the experiments in a viscous flow. It comes from the viscous effect due to the boundary layer around a wing section. The boundary layer on the suction side of a wing section grows thicker than the one on the pressure side, when the wing section has some angle of attack against a viscous flow. Such unequality in the boundary layer thickness hydrodynamically brings the virtual reduction of the attack angle as well as the camber ratio of a wing section due to the decline of the nose-tail line, or effectively distorts the section shape so that the trailing edge should be slightly raised up from the original. The author proposes a practical method to form the distorted wing section, in which the experimental slope of lift curve is utilized, and by which the pressure distribution can be computed for a wing section in a real flow. The pressure distribution thus computed for an exemplified wing section is in rather good agreement with the experimental result. (Wassmann)
A method to compute the pressure distribution on a wing section, using the experimental slope of lift curve
Methode zur Berechnung der Druckverteilung in einem Fluegelbereich mit Hilfe der experimentell ermittelten Steigung der Sogkurve
Journal of the Kansai Society of Naval Architects ; 177 ; 75-81
1980
7 Seiten, 7 Bilder, 13 Quellen
Article (Journal)
English
Prediction of Delta Wing Leading-Edge Vortex Circulation and Lift-Curve Slope
Online Contents | 1997
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