A method for calculating parallel blade vortex interaction (BVI) has been developed. The technique is based on the application of a three-dimensional aeroacoustic boundary element formulation using Analytical/Numerical Matching in conjunction with a recently developed viscous core trailing vortex roll-up model. Computational parameters were chosen to correspond with an experimental investigation conducted at NASA Ames Research Center modeling parallel BVI between a model rotor and an independently generated trailing vortex. Calculations include rotor blade chordwise pressure distributions, blade surface pressure time histories, and both near- and far-field radiated acoustic pressure time histories. Comparisons with experimental data demonstrate the feasibility of applying linear theory to the study of BVI.


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    Title :

    Unsteady compressible boundary element calculations of parallel blade-vortex interaction


    Additional title:

    Instationäre kompressible Rand-Element-Berechnungen von parallelen Rotorblatt-Wirbel-Interaktionen


    Contributors:
    Rule, J.A. (author) / Epstein, R.J. (author) / Bliss, D.B. (author)

    Published in:

    Publication date :

    1999


    Size :

    10 Seiten, 13 Bilder, 48 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Unsteady Compressible Boundary Element Calculations of Parallel Blade-Vortex Interaction

    Epstein, R. J. / Rule, J. A. / Bliss, D. B. et al. | British Library Conference Proceedings | 1998



    Parallel blade-vortex interaction

    Wilder, M.C. / Telionis, D.P. | Tema Archive | 1998