The invention relates to a trailing edge flap system useful in increasing low speed lift and low speed roll control in supersonic aircraft. Two trailing edge flaps (upper and lower) extend from the aircraft's engine exhaust nozzle. In the high lift mode of operation, a diverter block pushes the upper flap away from the nozzle, thereby exposing a flow passageway. Exhaust flow through the passageway tends to decrease boundary layer separation. To provide propulsive lateral control, the diverter block of one wing may be selectively closed, thereby reducing the lift on that wing.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Propulsive Lateral Control Nozzle


    Contributors:
    P. L. Coe (author) / A. B. Graham (author)

    Publication date :

    1980


    Size :

    9 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Experimental investigations of a nozzle-wing propulsive-lift concept

    WHITTEN, P. / KENNON, I. / STUMPFL, S. | AIAA | 1976


    Propulsive lander control system

    Mankovitz, R. J. | NTRS | 1965


    System, apparatus, and methods for a nosecone and propulsive nozzle

    JANEKE CHARL E | European Patent Office | 2023

    Free access

    Aerodynamical Aspects of Propulsive Nozzle Flow in Off-Design Regime

    Reijasse, P. | British Library Conference Proceedings | 1999


    PERFORMANCE EVALUATIONS OF THE STRATOFLY MR3 PROPULSIVE NOZZLE AT SUPERSONIC SPEEDS

    Nista, Ludovico / Ozden, Aysu / Saracoglu, Bayindir H. | TIBKAT | 2020