Tests were made in the NASA-Ames 40- by 80 Foot Wind Tunnel of a wing semispan with a nacelle (no propeller) from a typical, general aviation twin-engine aircraft. Measurements were made of the effect on drag of the cooling air flow through the nacelle. Internal and external nacelle pressures were measured. It was found that the cooling flow accounts for about 13% of the estimated airplane drag and about 42% of the cooling flow drag is associated with the internal flow. It was concluded that improvements could be made by relocating both the inlet and the outlet of the cooling air.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Full-scale wind tunnel study of nacelle shape on cooling drag


    Contributors:

    Conference:

    American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting ; 1979 ; New York, NY


    Publication date :

    1979-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Full-scale wind tunnel study of nacelle shape on cooling drag

    CORSIGLIA, V. / KATZ, J. / KROEGER, R. | AIAA | 1979


    Full-Scale Wind-Tunnel Study of the Effect of Nacelle Shape on Cooling Drag

    Corsiglia, Victor R. / Katz, Joseph / Kroeger, Richard A. | NTRS | 1981


    Full-scale Wind-Tunnel Study of the Effect of Nacelle Shape on Cooling Drag

    Victor R. Corsiglia / Joseph Katz / Richard A. Kroeger | AIAA | 1981


    Full-Scale Wind-Tunnel Study of the Effect of Nacelle Shape on Cooling Drag

    V. R. Corsiglia / J. Katz / R. A. Kroeger | NTIS | 1981