High-temperature luminescent coatings are being developed and applied for simultaneous pressure and temperature mapping in conventional-type hypersonic wind tunnels, providing global pressure as well as Global aeroheating measurements. Together, with advanced model fabrication and analysis methods, these techniques will provide a more rapid and complete experimental aerodynamic and aerothermodynamic database for future aerospace vehicles. The current status in development of simultaneous pressure- and temperature-sensitive coatings and measurement techniques for hypersonic wind tunnels at Langley Research Center is described. and initial results from a feasibility study in the Langley 31-Inch Mach 10 Tunnel are presented.


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    Title :

    Simultaneous Global Pressure and Temperature Measurement Technique for Hypersonic Wind Tunnels


    Contributors:
    G. M. Buck (author)

    Publication date :

    2000


    Size :

    14 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English