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CARS temperature measurements in a hypersonic propulsion test facilityStatic-temperature measurements performed in a reacting vitiated air-hydrogen Mach-2 flow in a duct in Test Cell 2 at NASA LaRC by using a coherent anti-Stokes Raman spectroscopy (CARS) system are discussed. The hypersonic propulsion Test Cell 2 hardware is outlined with emphasis on optical access ports and safety features in the design of the Test Cell. Such design considerations as vibration, noise, contamination from flow field or atmospheric-borne dust, unwanted laser- and electrically-induced combustion, and movement of the sampling volume in the flow are presented. The CARS system is described, and focus is placed on the principle and components of system-to-monochromator signal coupling. Contour plots of scramjet combustor static temperature in a reacting-flow region are presented for three stations, and it is noted that the measurements reveal such features in the flow as maximum temperature near the model wall in the region of the injector footprint.
Document ID
19910035171
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jarrett, O., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Smith, M. W.
(NASA Langley Research Center Hampton, VA, United States)
Antcliff, R. R.
(NASA Langley Research Center Hampton, VA, United States)
Northam, G. B.
(NASA Langley Research Center Hampton, VA, United States)
Cutler, A. D.
(George Washington University Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
November 1, 1990
Subject Category
Instrumentation And Photography
Accession Number
91A19794
Distribution Limits
Public
Copyright
Other

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