Reducing or eliminating the operational restrictions of supersonic aircraft over populated areas has led to extensive research at NASA. Restrictions are due to the disturbance of the sonic boom, caused by the coalescence of shock waves formed off the aircraft. Recent work has been performed to reduce the magnitude of the sonic boom N-wave generated by airplane components with focus on shock waves caused by the exhaust nozzle plume. Previous Computational Fluid Dynamics (CFD) analyses showed how the shock wave formed at the nozzle lip interacted with the nozzle boat-tail expansion wave. The nozzle lip shock moved with increasing nozzle pressure ratio (NPR) and reduced the nozzle boat-tail expansion. Lip shock movement caused a favorable change in the observed pressure signature. These results were applied to a simplified supersonic vehicle geometry with no inlets and no tail, in which the goal was to demonstrate how under-expanded nozzle operation reduced the sonic boom signature by twelve percent. A secondary goal was to demonstrate the use of the Cart3D inviscid code for off-body pressure signatures including the nozzle plume effect.


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    Title :

    Analysis of Exhaust Plume Effects on Sonic Boom for a 59-Degree Wing Body Model


    Contributors:

    Conference:

    49th AIAA Aerospace Sciences Meeting ; 2011 ; Orlando, FL, United States


    Publication date :

    2011-01-06


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :




    ANALYSIS OF EXHAUST PLUME EFFECTS ON SONIC BOOM FOR A 59-DEGREE WING BODY MODEL

    Castner, R. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2011


    Exhaust Plume Effects on Sonic Boom for a Delta Wing and Swept Wing-Body Model

    Castner, R. / Lake, T. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2012