Infrared thermography was used to obtain data on the state of the boundary layer of a natural laminar flow airfoil in supersonic flight. In addition to the laminar-to-turbulent transition boundary, the infrared camera was able to detect shock waves and present a time dependent view of the flow field. A time dependent heat transfer code was developed to predict temperature distributions on the test subject and any necessary surface treatment. A commercially available infrared camera was adapted for airborne use in this application. Readily available infrared technology has the capability to provide detailed visualization of various flow phenomena in subsonic to hypersonic flight regimes.


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    Title :

    Visualization of In-Flight Flow Phenomena Using Infrared Thermography


    Contributors:
    D. W. Banks (author) / C. P. vanDam (author) / H. J. Shiu (author) / G. M. Miller (author)

    Publication date :

    2000


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Visualization of In-Flight Flow Phenomena Using Infrared Thermography

    Banks, D. W. / vanDam, C. P. / Shiu, H. J. et al. | NTRS | 2000


    In-Flight Flow Visualization Using Infrared Thermography

    C. P. vanDam / H. J. Shiu | NTIS | 1997


    In-Flight Flow Visualization Using Infrared Thermography

    vanDam, C. P. / Shiu, H. J. / Banks D. W. | NTRS | 1997


    Remote Infrared Thermography for In-Flight Flow Diagnostics

    Shiu, H. J. / vanDam, C. P. | NTRS | 1999


    In-flight flow visualization using infrared imaging

    BRANDON, J. / MANUEL, G. / WRIGHT, JR., R. et al. | AIAA | 1988