A small-disturbance transonic analysis code is used to calculate the flow-field effects of adding an engine nacelle to a wing/body configuration. Analyses are performed on an advanced transport configuration with and without engine nacelles. Two nacelle shapes are analyzed and the effects of the nacelle installation on pressure distributions are compared with experimental results obtained by shifting the nacelle longitudinally and vertically relative to the wing. Effects of varying the nacelle installation yaw angle are also analyzed and compared with experimental data. These comparisons show that the analysis code is adequately sensitive to variations in nacelle shape, longitudinal and vertical location beneath the wing, and the nacelle installation yaw angle. Results indicate that the code can be used as an effective guide during the design process.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Computational analysis for an advanced transport configuration with engine nacelle


    Beteiligte:

    Erscheinungsdatum :

    01.07.1983


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Engine nacelle

    FULAYTER ROY D / SMITH III CRAWFORD F | Europäisches Patentamt | 2019

    Freier Zugriff



    Aerodynamic Investigations of an Advanced Over-the-Wing Nacelle Transport Aircraft Configuration

    Hill, Geoffrey A. / Kandil, Osama A. / Hahn, Andrew S. | AIAA | 2009