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    Aerodynamic effects of nearly uniform slipstreams on thin wings in the transonic regime (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152351
    Format: application/pdf
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