Two alternative approaches are developed to calculate blade-vortex interaction airloads on helicopter rotors: second order lifting-line theory, and a lifting surface theory correction. The common approach of using a larger vortex core radius to account for lifting-surface effects is quantified. The second order lifting-line theory also improves the modeling of yawed flow and swept tips. Calculated results are compared with wind tunnel measurements of lateral flapping, and with flight test measurements of blade section lift on SA349/2 and H-34 helicopter rotors. The tip vortex core radius required for good correlation with the flight test data is about 20 percent chord, which is within the range of measured viscous core sizes for helicopter rotors.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Wake Model for Helicopter Rotors in High Speed Flight


    Beteiligte:
    W. R. Johnson (Autor:in)

    Erscheinungsdatum :

    1988


    Format / Umfang :

    305 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Free wake aerodynamic analysis of helicopter rotors

    Morino, L. / Kaprielian, Z. / Spicic, S.R. | Tema Archiv | 1983


    High-speed noise of helicopter rotors

    Shenoy, K. R. | NTRS | 1982


    Wake-Coupling CFD-CSD Analysis of Helicopter Rotors in Steady and Maneuvering Flight Conditions

    Thomas, S. / Ananthan, S. / Baeder, J.D. et al. | British Library Conference Proceedings | 2010


    A State-Space Free-Vortex Hybrid Wake Model For Helicopter Rotors

    Wasileski, B.J. / Peters, D.A. / AHS international | British Library Conference Proceedings | 2008