Surface heat-transfer measurements inside a supersonic combustor by LIF

K. Kontis

Surface heat-transfer measurements inside a supersonic combustor by LIF

K. Kontis

Research output: Chapter in Book/Conference proceeding › Conference 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 language	English
Title of host publication	8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference\|8th AIAA/ASME Jt. Thermophys. Heat Transf. Conf.
Publication status	Published - 2002
Event	8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference 2002 - St. Louis, MO Duration: 1 Jul 2002 → …

Conference

Conference	8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference 2002
City	St. Louis, MO
Period	1/07/02 → …

Cite this

@inproceedings{c7030c4b1dfb4ba9ad7269e40ce01b49,

title = "Surface heat-transfer measurements inside a supersonic combustor by LIF",

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. {\textcopyright} 2002 by K. Kontis. Published by the American Institute of Aeronautics and Astronautics, Inc.",

author = "K. Kontis",

year = "2002",

language = "English",

isbn = "9781624101182",

booktitle = "8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference|8th AIAA/ASME Jt. Thermophys. Heat Transf. Conf.",

note = "8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference 2002 ; Conference date: 01-07-2002",

}

TY - GEN

T1 - Surface heat-transfer measurements inside a supersonic combustor by LIF

AU - Kontis, K.

PY - 2002

Y1 - 2002

N2 - 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.

AB - 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.

M3 - Conference contribution

SN - 9781624101182

BT - 8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference|8th AIAA/ASME Jt. Thermophys. Heat Transf. Conf.

T2 - 8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference 2002

Y2 - 1 July 2002

ER -

Surface heat-transfer measurements inside a supersonic combustor by LIF

Abstract

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