An experimental investigation of the in-ground effect aerodynamic characteristics and predicted landing-ground-roll performance of wing-canard fighter configuration with a secondary nozzle thrust reverser was completed. These tests were conducted in the Langley 14 by 22 foot Subsonic Wind Tunnel using a model equipped with a pneumatic jet for thrust simulation of nozzle pressure ratios up to 4.0. The model was tested in the landing rollout configuration at approx. wheel touchdown height for a range of decreasing dynamic pressure from 50 psf down to 10 psf. Landing-ground-roll predictions of the configuration were calculated using the wind tunnel results.


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    Title :

    Aerodynamics in Ground Effect and Predicted Landing Ground Roll of a Fighter Configuration with a Secondary-Nozzle Thrust Reverser


    Contributors:
    D. W. Banks (author)

    Publication date :

    1988


    Size :

    131 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English