The paper describes the theoretically based activities conducted during the first year of the European Brite-EuRam HELIFUSE programme. These activities mainly consisted of the numerical prediction of helicopter fuselage flowfields with existing Navier-Stokes solvers on a number of pre-selected test cases, taken out of an extensive wind tunnel test programme. These calculations were conducted in parallel at three National Research Institutes (CIRA, DLR and ONERA), three Helicopter Manufacturers (AGUSTA, EUROCOPTER and GKN-WESTLAND), one Software Company (SIMULOG) and two Universities (DTU and IAG). They were aimed at simulating the flowfield around simplified geometric configurations of the EUROCOPTER DGV (high-speed Dauphin) fuselage. Simultaneously, wind tunnel tests were performed in the ONERA pressurized F1 wind tunnel. These tests covered the full range of Reynolds numbers from those characteristic of small-scale models to those characteristic of actual flight conditions. Comparison of the blind-test calculations with experimental data show that, although most of the methods give a good prediction of the pressure distribution on the fuselage, none of them is able to predict either the Reynolds number influence on fuselage drag or to estimate with sufficient accuracy the fuselage drag variation due to shape modification.


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    Title :

    Navier-Stokes calculations of helicopter fuselage flowfield and loads


    Contributors:
    Costes, M. (author) / Collercandy, R. (author) / Kroll, N. (author) / Geyr, H. Freiherr von (author) / Renzoni, P. (author) / Amato, M. (author) / Kokkalis, A. (author) / Rocchetto, A. (author) / Serr, C. (author) / Larrey, E. (author)


    Publication date :

    1998


    Size :

    14 Seiten, 22 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English