As scramjet engine development moves toward higher and higher speeds, it will be important to continue to ground test complete nose-to-tail configurations at true flight conditions. Above Mach 10, the freestream total pressure requirements can only be met by an expansion-tube facility. To establish the practicality of ground-testing complete scramjet configurations at high Mach numbers, an expansion-tunnel facility is used to test a generic two-dimensional scramjet at a Mach 10 replication condition. As the flow produced in an expansion-tube facility is transient in nature, a method for analyzing point measurements within the scramjet is developed. A transient numerical simulation ofthe engine configuration without fuel injection is used to verify the validity of the technique, as well as to provide a reference data set for comparison to experimental data. These experiments show that stable supersonic combustion is established during the test time. Using the developed transient analysis, accurate quasi-steady pressure data at true flight conditions can be inferred from scramjet test measurements in an expansion-tube facility.


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    Title :

    Scramjet experiments in an expansion tunnel: Evaluated using a quasi-steady analysis technique


    Additional title:

    Scramjet-Experimente in einem Expansionstunnel: Auswertung mit Hilfe einer quasistatischen Analyse


    Contributors:

    Published in:

    AIAA Journal ; 48 , 8 ; 1635-1646


    Publication date :

    2010


    Size :

    12 Seiten, 14 Bilder, 23 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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