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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    Titel :

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


    Beteiligte:
    Lv, Zhong (Autor:in) / Xia, Zhi-xun (Autor:in) / Liu, Bing (Autor:in) / Liu, Yuan-chun (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2015-12-09


    Format / Umfang :

    6 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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