A new scramjet configuration using solid fuel as propellant is proposed, namely, the solid-fuel rocket scramjet. Experimental and numerical investigation of the solid-fuel rocket scramjet combustor was conducted to evaluate its performance. The experiment simulated a flight environment of Mach 4 at a 17 km altitude. Magnesium-based solid fuel was used as propellant in this study. The results show that secondary combustion occurs in supersonic combustor. The combustion efficiency of the propellant is about 65%, and the total pressure recovery is about 0.5. These imply that the scramjet configuration using solid fuel as a propellant is feasible. The results of the numerical analysis show that a normal shock wave is generated in the core flow of the combustor, and this is due to all of the fuel-rich gas being injected in the same cross section.


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    Title :

    Experimental and Numerical Investigation of a Solid-Fuel Rocket Scramjet Combustor


    Contributors:
    Lv, Zhong (author) / Xia, Zhi-xun (author) / Liu, Bing (author) / Liu, Yuan-chun (author)

    Published in:

    Publication date :

    2016-03-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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