Surface heat-transfer measurements inside a supersonic combustor by LIF

K. Kontis

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Abstract

    A study has been conducted to measure surface temperatures inside a model rectangular supersonic combustor using a technique exploiting the fluorescence properties of Dy:YAG by LIF. The wind tunnel was a blown down type using vitiated air with nominal conditions at the entrance of the test section M∞=2.5, Po=5×105 N/m2, To=800 K and Re∞/m=9.6×106. Fuel was hydrogen gas in room temperature injected parallel to the tunnel through a fuel injector slit located along the backward surface of a step. The results under hot flow conditions were compared with numerical simulations performed using a 2-D Navier-Stokes code with full chemistry. © 2002 by K. Kontis. Published by the American Institute of Aeronautics and Astronautics, Inc.
    Original languageEnglish
    Title of host publication8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference|8th AIAA/ASME Jt. Thermophys. Heat Transf. Conf.
    Publication statusPublished - 2002
    Event8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference 2002 - St. Louis, MO
    Duration: 1 Jul 2002 → …

    Conference

    Conference8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference 2002
    CitySt. Louis, MO
    Period1/07/02 → …

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