A free-piston shock tunnel has been used to obtain test data on a scramjet combustion chamber with sidewall injection. The results obtained indicate that combustion was strongly influenced by a region of fuel whose temperature was held below its ignition temperature by wall-cooling effects; this increased the fraction of unburned fuel and resulted in a significant loss of specific impulse. Aerodynamic heating would keep the walls above hydrogen ignition temperature in an actual scramjet powerplant, however. Maximum specific impulse was obtained with a combination of parallel and transverse injection in a long combustion chamber, followed by a dual stage expansion.


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    Title :

    Hydrogen scramjet with sidewall injection - Shock tunnel simulations


    Contributors:
    Morgan, R. G. (author) / Paull, A. (author) / Morris, N. (author) / Stalker, R. J. (author)

    Publication date :

    1987-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





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