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A criterion for leading-edge separation

Published online by Cambridge University Press:  26 April 2006

E. O. Tuck
E. O. Tuck
Affiliation:
Applied Mathematics Department, University of Adelaide, Adelaide, South Australia 5001
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Abstract

The maximum angle of attack for unseparated flow over an airfoil of chord c with finite nose radius of curvature r is shown to be 0.818(r/c)½

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 222 , January 1991 , pp. 33 - 37
Copyright
© 1991 Cambridge University Press

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References

Abbott, I. H. & Von Doenhoff, A. E.: 1958 Theory of Wing Sections. Dover.
Hurley, D. G.: 1989 Mathematical research at the Aeronautical Research Laboratories 1939–1960. J. Austral. Math. Soc. B 30, 389–413.Google Scholar
Lighthill, M. J.: 1951 A new approach to thin aerofoil theory. Aeronaut. Q. 3, 193–210.Google Scholar
Moriarty, J. A. & Tuck, E. O., 1989 Thin aerofoils with high-incidence flaps or blunt trailing edges. Aeronaut. J. 93, 93–99.Google Scholar
Newman, J. N.: 1977 Marine Hydrodynamics. M. I. T. Press.
Tulin, M. P. & Hsu, C. C., 1980 New applications of cavity flow theory. In 13th Symp. Naval Hydrodynamics, Tokyo, pp. 107–131. Proceedings, ONR, Washington DC.
Van Dyke, M. 1956 Second-order subsonic airfoil theory including edge effects. NACA Rep. 1274.Google Scholar
Van Dyke, M. 1964 Perturbation Methods in Fluid Mechanics. Academic.
Werle, M. J. & Davis, R. T., 1972 Incompressible laminar boundary layers on a parabola at angle of attack: a study of the separation point. Trans. ASME E: J. Appl. Mech. 7–12.Google Scholar