An engine test facility was constructed at the NASA Langley Research Center in support of a supersonic combustion ramjet (scramjet) technology development program. Hydrogen combustion in air with oxygen replenishment provides simulated air at Mach 4 flight velocity, pressure, and true total temperature for an altitude range from 57,000 to 86,000 feet. A facility nozzle with a 13 in square exit produces a Mach 3.5 free jet flow for engine propulsion tests. The facility is described and calibration results are presented which demonstrate the suitability of the test flow for conducting scramjet engine research.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Langley Mach 4 Scramjet Test Facility


    Beteiligte:

    Erscheinungsdatum :

    1985-02-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Langley Mach 4 Scramjet Test Facility

    E. H. Andrews / M. G. Torrence / G. Y. Anderson et al. | NTIS | 1985


    Operating Characteristics of the Langley Mach 7 Scramjet Test Facility

    R. W. Guy / M. G. Torrence / A. P. Sabol et al. | NTIS | 1981


    Operating characteristics of the Langley Mach 7 Scramjet Test Facility

    Guy, R. W. / Torrence, M. G. / Sabol, A. P. et al. | NTRS | 1981