A panel method based model for the computation of the time averaged influence of a propeller slipstream on the aerodynamic characteristics of an aircraft configuration is described. The slipstream model is based on the simplifications that the single rotating propeller is replaced by an actuator disk and that all the vorticity of the slipstream is represented on a cylindrical sheet of fixed geometry which envelops the slipstream in combination with a discrete vortex at the axis of the slipstream. Appropriate jump conditions across the actuator disk and boundary conditions on the cylindrical sheet, solved simultaneously with the boundary conditions on the aircraft configuration, yield the mutual influence of the propeller and the slipstream on the aerodynamic characteristics of the aircraft. This slipstream model is incorporated in a three dimensional panel method. Computed lift increments due to the slipstream are presented for a realistic wing/nacelle/fuselage configuration and compared with wind tunnel data for several thrust coefficients and angles of attack of the aircraft.


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    Titel :

    Aerodynamic Analysis of Slipstream/Wing/Nacelle Interference for Preliminary Design of Aircraft Configurations


    Beteiligte:
    C. M. Vanbeek (Autor:in) / W. J. Piers (Autor:in) / B. Oskam (Autor:in)

    Erscheinungsdatum :

    1991


    Format / Umfang :

    25 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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