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Coherent anti-Stokes Raman spectroscopy temperature measurements in a hydrogen-fueled supersonic combustorCoherent anti-Stokes Raman spectroscopy (CARS) thermometry has been used to obtain static temperature cross sections in a three-dimensional supersonic combustor flowfield. Data were obtained in three spanwise planes downstream of a single normal fuel injector which was located downstream of a rearward-facing step. The freestream flow was nominally Mach 2 and was combustion heated to a total temperature of 1440 K (yielding a static temperature of about 800 K in the freestream) to simulate the inflow to a combustor operating at a flight Mach number of about 5.4. Since a broadband probe laser was used an instantaneous temperature sample was obtained with each laser shot at a repetition rate of 10 Hz. Thus root-mean-square (rms) temperatures and temperature probability density functions (pdf's) were obtained in addition to mean temperatures.
Document ID
19930047967
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Smith, Michael W.
(NASA Langley Research Center Hampton, VA, United States)
Jarrett, Olin, Jr.
(NASA Langley Research Center Hampton, VA, United States)
Antcliff, Richard R.
(NASA Langley Research Center Hampton, VA, United States)
Northam, G. B.
(NASA Langley Research Center Hampton, VA, United States)
Cutler, Andrew D.
(George Washington Univ. Hampton, VA, United States)
Taylor, David J.
(Los Alamos National Lab. NM, United States)
Date Acquired
August 16, 2013
Publication Date
April 1, 1993
Publication Information
Publication: Journal of Propulsion and Power
Volume: 9
Issue: 2
ISSN: 0748-4658
Subject Category
Inorganic And Physical Chemistry
Accession Number
93A31964
Distribution Limits
Public
Copyright
Other

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