The pressure recovery of incoming cooling air and the drag associated with engine cooling of a typical general aviation twin-engine aircraft was investigated experimentally. The semispan model was mounted vertically in the 40- by 80-Foot Wind Tunnel at Ames Research Center. The propeller was driven by an electric motor to provide thrust with low vibration levels for the cold-flow configuration. It was found that the propeller slipstream reduces the frontal air spillage around the blunt nacelle shape. Consequently, this slipstream effect promotes flow reattachment at the rear section of the engine nacelle and improves inlet pressure recovery. These effects are most pronounced at high angles of attack, that is, climb condition. For the cruise condition those improvements were more moderate.


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    Title :

    Effect of propeller slipstream on the drag and performance of the engine cooling system for a general aviation twin-engine aircraft


    Contributors:
    Katz, J. (author) / Corsiglia, V. R. (author) / Barlow, P. R. (author)

    Conference:

    Aircraft Systems Meeting ; 1980 ; Anaheim, CA


    Publication date :

    1980-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English








    Full-Envelope Aerodynamics Modeling of a General Aviation Aircraft with Propeller Slipstream Effects

    Ralston, J. / Hultberg, R. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2010