The aim of this paper is to present aerodynamic analyses of realistic fuselage configurations using computational fluid dynamics. A development model of the Ansat helicopter is employed. The model is tested at the subsonic wind tunnel of the Kazan National Research Technical University/Kazan Aviation Institute for a range of Reynolds numbers, pitch, and yaw angles. The computational fluid dynamics results were found to be in fair agreement with the test data and revealed flow separation at the rear of the fuselage. Once confidence in the computational fluid dynamics method was established, further modifications were introduced to the fuselage model to demonstrate drag reduction via small shape changes. The contribution to the overall drag from each fuselage part and the interference drag between the main fuselage components were also investigated.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Computational Fluid Dynamics Modeling of Helicopter Fuselage Drag


    Beteiligte:
    Batrakov, A. (Autor:in) / Garipova, L. (Autor:in) / Kusyumov, A. (Autor:in) / Mikhailov, S. (Autor:in) / Barakos, G. (Autor:in)

    Erschienen in:

    Journal of Aircraft ; 52 , 5 ; 1634-1643


    Erscheinungsdatum :

    2015-07-03


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Aerodynamic Drag Prediction of Helicopter Fuselage

    A. Filippone / J. A. Michelsen | AIAA | 2001


    Experimental Study of Helicopter Fuselage Drag

    Stepanov, Robert | Online Contents | 2016


    Experimental Study of Helicopter Fuselage Drag

    Stepanov, Robert / Zherekhov, Vladimir / Pakhov, Vladimir et al. | AIAA | 2016


    A Computational Framework for Helicopter Fuselage Drag Reduction Using Vortex Generators

    Boniface, J. / American Helicopter Society | British Library Conference Proceedings | 2014