A sonic control device that reduces the effects of shock waves generated by an aircraft traveling at supersonic speeds. The control device includes a control surface located at or near the nose section of the aircraft. The position of the control surface can be moved between a retracted position and an extended position. When in a deflected position, the control surface increases the air pressure at the nose section. The increase in air pressure at the nose section decreases both the pressure amplitude and the slope of the overall shock wave as the wave travels toward the ground. Additionally, the deflection of the control surface may induce a downward directed pressure increase which creates less of a drag penalty than a truly blunt nose. When shock control is not desired, the control surface is moved back to the retracted position to reduce the drag on the plane. The moving control device allows a supersonic aircraft to efficiently travel above both land and water.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Low sonic boom shock control/alleviation surface


    Beteiligte:

    Erscheinungsdatum :

    21.04.1998


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Sonic Boom Alleviation Using Keel Configurations

    Marconi, F. | Online Contents | 2003


    Sonic Boom Alleviation Using Keel Configurations

    Frank Marconi / Rodney D. W. Bowersox / Joseph A. Schetz | AIAA | 2003