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 secondary-flow boundary-layer solutions are obtained for an elliptical fuselage-wing-tail cross section. (Jensen)
Boundary-layer-induced secondary flows on wing-body configurations
Grenzschichtinduzierte Sekundaerstroemungen an verschiedenen Tragfluegel- und Rumpfformen und deren Zusammenwirkung
AIAA Journal ; 18 , 1 ; 55-62
1980
8 Seiten, 10 Bilder, 11 Quellen
Aufsatz (Zeitschrift)
Englisch
Boundary layer induced secondary flows due to wing-body interference
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