An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the performance of nonaxisymmetric-nozzle thrust reversers installed on a generic twin-engine fighter aircraft model. Test data were obtained at static conditions and at Mach numbers from 0.15 to 1.20 with jet exhaust simulated by high pressure air. Results showed that reverse-thrust levels of greater than 50 percent at static conditions and greater than 30 percent at in-flight conditions could be achieved. Internal reverser-port passage length was found to be very important in improving reverser performance. Increasing the reverser-port passage length improved reverse-thrust performance by as much as 28 percent at static conditions and by as much as 17 percent at Mach 1.20.


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    Title :

    Aeropropulsive Characteristics of Nonaxisymmetric-Nozzle Thrust Reversers at Mach Numbers from 0 to 1.20


    Contributors:
    G. T. Carson (author) / F. J. Capone (author) / M. L. Mason (author)

    Publication date :

    1984


    Size :

    126 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English