At supersonic Mach numbers, variable geometry is required to provide efficient compression of free-stream air and to match inlet corrected airflow with engine corrected airflow requirements; shock control systems considered; integral control of normal shock position; integral control of normal shock position plus lead compensation; and integral control of normal shock position plus diffuser-exit Mach number anticipation.


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    Title :

    Effect of inlet normal shock position control systems on range of supersonic transports


    Additional title:

    SAE -- Paper


    Contributors:

    Conference:

    SAE Meeting ; 1961 Inlets



    Publication date :

    1961


    Size :

    11 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English