Stall Flutter of a Thin Aerofoil with Leading Edge Separation

A theoretical investigation about unsteady aerodynamic forces acting on a thin vibrating aerofoil with leading edge separation is presented on the assumption that unsteady component of velocity is small compared with velocity of uniform flow, and flow separates from the leading edge smoothly. In thi...

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Bibliographic Details
Published in:Bulletin of JSME 1974, Vol.17(107), pp.578-586
Main Authors: SHINOHARA, Kenji, TANAKA, Hideo, HANAMURA, Yoji
Format: Article
Language:English
Online Access:Get full text
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Summary:A theoretical investigation about unsteady aerodynamic forces acting on a thin vibrating aerofoil with leading edge separation is presented on the assumption that unsteady component of velocity is small compared with velocity of uniform flow, and flow separates from the leading edge smoothly. In this theory is taken into consideration the effect of disturbance in the wake. But the unsteady aerodynamic forces due to the karman vortex street which has a close relation to a separated flow are neglected for the reason that the effect of Karman vortex street on the stall flutter can be separated from the effect of pure aerodynamic forces due to blade vibration in the greater part of angles of attack. Agreements between computational and experimental results are satisfactory for a relatively small reduced frequency.
ISSN:0021-3764
1881-1426
DOI:10.1299/jsme1958.17.578