An investigation has been conducted in the Langley 16-foot transonic tunnel to verify analytically predicted benefits in climb and cruise performance due to blowing the jet exhaust over the wing for a transport configuration. A wing-body model - powered-nacelle rig combination was tested at Mach numbers of 0.5 and 0.8 at angles of attack from -2 to 4 deg and jet total pressure ratios from jet off to 3 or 4 (depending on Mach number) for a variety of nacelle locations relative to the wing. Results from this investigation show that the induced drag for the wing-body (nacelles were nonmetric) was reduced for virtually all configurations. In addition to the experimental results, comparisons of the data with available prediction methods are included to show their validity and capabilities.


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    Title :

    An investigation of induced drag reduction through over-the-wing blowing


    Contributors:

    Conference:

    Propulsion Conference ; 1977 ; Orlando, FL, US


    Publication date :

    1977-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English