Method of operating shock tunnel, with free-piston compression of driver gas, is presented; it is shown that tailored interface operation can be achieved at high shock speeds, combined with generation of high stagnation pressures at entrance to hypersonic nozzle; free-piston shock tunnel is described, and experiments are reported in which helium driver gas is used to achieve tailored interface operation at shock Mach numbers of up to 18.5 in air; it is concluded that enthalpy simulation of flight, at speeds in excess of orbital velocity, can be achieved with this type of shock tunnel.


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    Title :

    Study of free-piston shock tunnel


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 5 , n 12


    Publication date :

    1967


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    A study of the free-piston shock tunnel.

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