Slender body theory is combined with higher-order boundary layer concepts in order to determine the boundary layer induced potential flow over wing-body cylindrical cross-sections. It is shown that the three-dimensional viscous displacement flowfield can be evaluated, in the vicinity of the surface of the cylinder, by a quasi-two-dimensional slender body procedure. This approximation is valid when the boundary layer is thin, the body is 'slender' in the usual inviscid sense, and there are no geometrical discontinuities. The induced potential flow is determined by conformal mapping techniques. These solutions are obtained in closed form or by quadratures. Complete second-order boundary layer solutions are obtained for an elliptical fuselage - wing-tail cross-section. (Kursetz)
Boundary layer induced secondary flows due to wing-body interference
Grenzschichtausgeloeste sekundaere Stroemungen in der Interferenz zwischen Fluegel und Koerper
AIAA-Papers ; Jan ; 1-11
1979
11 Seiten, 13 Bilder, 11 Quellen
Conference paper
English
Boundary-layer-induced secondary flows on wing-body configurations
Tema Archive | 1980
|Supersonic Wing/Body Interference
British Library Online Contents | 1994
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