The application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the SVC method, a secondary air flow injection close to the nozzle exit generates an asymmetry in the wall pressure distribution and side-loads on the nozzle, which are also lateral components of the thrust vector. SVC forcing of the axisymmetric nozzle generates fully three-dimensional flows with very complex structures that interact with the external flow. In the present work, the experimental data on a nozzle designed and tested for a supersonic cruise aircraft are used for validating the numerical tool at different flight Mach numbers and nozzle pressure ratios. Then, an optimal position for the slot is sought and the fully 3D flow at flight Mach number M∞=0.9 is investigated numerically for different values of the SVC forcing.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method



    Erscheinungsdatum :

    01.01.2021



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Klassifikation :

    DDC:    621



    Thrust Vectoring using Differential Throttling in Axisymmetric Aerospike Nozzle

    Marsilio, Roberto / Resta, Emanuele / Di Cicca, Gaetano et al. | AIAA | 2024





    Thrust vectoring produced by supersonic nozzle with oblique exit plane

    Dunn, B.M. / Emery, A.F. | Engineering Index Backfile | 1966