The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom were determined. The problem resolves itself into the solution of certain definite integrals, which were identified as Bessel functions of the first and second kind, and of zero and first order. The theory, 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 was analyzed. An exact solution, involving potential flow and the adoption of the Kutta condition, was derived. The solution is of a simple form and is expressed by means of an auxiliary parameter k. The flutter velocity, treated as the unknown quantity, was determined as a function of a certain ratio of the frequencies in the separate degrees of freedom for any magnitudes and combinations of the airfoil-aileron parameters.


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    Title :

    General Theory of Aerodynamic Instability and the Mechanism of Flutter


    Contributors:


    Publication date :

    1979-12-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    General theory of aerodynamic instability and mechanism of flutter

    Theodorsen, T. | Engineering Index Backfile | 1935



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    Garrick, I. E. | TIBKAT | 1969



    Active Flutter Control Using Generalized Unsteady Aerodynamic Theory

    John W. Edwards / John V. Breakwell / Arthur E. Bryson | AIAA | 1978