A simplified model is used to describe the interaction between a propeller slipstream and a wing in the transonic regime. The undisturbed slipstream boundary is assumed to coincide with an infinite circular cylinder. The undisturbed slipstream velocity is rotational and is a function of the radius only. In general, the velocity perturbation caused by introducing a wing into the slipstream is also rotational. By making small disturbance assumptions, however, the perturbation velocity becomes nearly potential, and an approximation for the flow is obtained by solving a potential equation.


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    Title :

    Aerodynamic effects of nearly uniform slipstreams on thin wings in the transonic regime


    Contributors:
    Rizk, M. H. (author)

    Publication date :

    1980-05-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


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