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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Propulsive Lateral Control Nozzle


    Beteiligte:
    P. L. Coe (Autor:in) / A. B. Graham (Autor:in)

    Erscheinungsdatum :

    1980


    Format / Umfang :

    9 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Blast wave in a nozzle for propulsive applications

    Varsi, G. / Back, L. H. / Kim, K. | NTRS | 1976


    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 | Europäisches Patentamt | 2023

    Freier Zugriff

    Aerodynamical Aspects of Propulsive Nozzle Flow in Off-Design Regime

    Reijasse, P. | British Library Conference Proceedings | 1999