An aerodynamic computer code, capable of predicting unsteady and C sub m values for an airfoil undergoing dynamic stall, is used to predict the amplitudes and frequencies of a wing undergoing torsional stall flutter. The code, developed at United Technologies Research Corporation (UTRC), is an empirical prediction method designed to yield unsteady values of normal force and moment, given the airfoil's static coefficient characteristics and the unsteady aerodynamic values, alpha, A and B. In this experiment, conducted in the PSU 4' x 5' subsonic wind tunnel, the wing's elastic axis, torsional spring constant and initial angle of attack are varied, and the oscillation amplitudes and frequencies of the wing, while undergoing torsional stall flutter, are recorded. These experimental values show only fair comparisons with the predicted responses. Predictions tend to be good at low velocities and rather poor at higher velocities.


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    Titel :

    Application of an airfoil stall flutter computer prediction program to a three-dimensional wing: Prediction versus experiment


    Beteiligte:

    Erscheinungsdatum :

    1982-03-01


    Medientyp :

    Hochschulschrift


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



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    L. E. Ericsson / J. P. Reding | NTIS | 1971


    Unsteady airfoil stall and stall flutter

    Ericsson, L. E. / Reding, J. P. | NTRS | 1971


    Shock-Stall Flutter of a Two-Dimensional Airfoil

    Masahide Yamasaki / Koji Isogai / Takefumi Uchida et al. | AIAA | 2004


    Shock-stall flutter of a two-dimensional airfoil

    Yamasaki, M. / Isogai, K. / Uchida, T. et al. | Tema Archiv | 2004