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General Theory of Aerodynamic Instability and the Mechanism of FlutterThe aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom have been determined. The problem resolves itself into the solution of certain definite integrals, which have been identified as Bessel functions of the first and second kind and of zero and first order. The theory, being based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing-section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been arrived at. The solution is of a simple form and is expressed by means of an auxiliary parameter K.
Document ID
19930090935
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Report
Authors
Theodorsen, Theodore
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1949
Subject Category
Aerodynamics
Report/Patent Number
NACA-TR-496
Report Number: NACA-TR-496
Accession Number
93R20225
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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