A hardened CARS system utilized for temperature measurements in a supersonic combustorA coherent anti-Stokes Raman scattering (CARS) system has been hardened for utilization in a NASA Langley supersonic combustion test cell that can obtain temperature cross sections of the flow at three locations. This system is remotely operated and environmentally protected. Measurements were obtained in a scramjet combustor model consisting of a rearward-facing step, followed by an expansion duct. The freestream conditions were Mach 2, with static pressure that ranged from 0.8 to 1.9 atm, and a static temperature of about 800 K. Data for two different flow conditions were obtained that provided a comparison between reacting and nonreacting mixing of injected hydrogen fuel with the combustion-heated supersonic stream.
Document ID
19910034688
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Antcliff, Richard R. (NASA Langley Research Center Hampton, VA, United States)
Smith, Michael W. (NASA Langley Research Center Hampton, VA, United States)
Jarrett, Olin, Jr. (NASA Langley Research Center Hampton, VA, United States)
Northam, G. Burton (NASA Langley Research Center Hampton, VA, United States)
Cutler, Andrew D. (George Washington University Hampton, VA, United States)