Information on unsteady separation and dynamic stall is being obtained from two experimental programs that have been underway at United Technologies Research Center since 1984. The first program is designed to obtain detailed surface pressure and boundary layer condition information during high amplitude pitching oscillations of a large (17.3 in. chord) model wing in a wind tunnel. The second program involves the construction and testing of a pressure-instrumented model helicopter rotor. This presentation describes some of the results of these experiments, and in particular compares the detailed dynamic stall inception information obtained from the oscillating wing with the unsteady separation and reverse flow results measured on the retreating blade side of the model rotor during wind tunnel testing.


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    Titel :

    Unsteady separation experiments on 2-D airfoils, 3-D wings, and model helicopter rotors


    Beteiligte:


    Erscheinungsdatum :

    1992-03-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Unsteady Aerodynamics of Helicopter Rotors

    W. P. Jones / W. J. McCroskey / J. J. Costes | NTIS | 1972


    Unsteady aerodynamics of helicopter rotors

    Jones, W. P. / McCroskey, W. J. / Costes, J. J. | TIBKAT | 1972


    Unsteady Flow Modeling of Helicopter Airfoils

    Anikin, V.A. / Gerasimov, O.V. / Kritsky, B.S. | British Library Conference Proceedings | 2007