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Rocket plume flowfield characterization using laser Rayleigh scatteringA Doppler-resolved laser Rayleigh scattering diagnostic was applied to a 111 N thrust, regenerative and fuel-film cooled, gaseous hydrogen/gaseous oxygen rocket engine. The axial and radial mean gas velocities were measured from the net Doppler shifts observed for two different scattering angles. Translational temperatures and number densities were estimated from the Doppler widths and scattered intensities, respectively, by assuming that water was the dominant scattering species in the exhaust. The experimental results are compared with theoretical predictions from a full Navier-Stokes code (RD/RPLUS) and the JANNAF Two-Dimensional Kinetics (TDK) and Standardized Plume Flowfield (SPF-II) codes. Discrepancies between the measured and predicted axial velocities, temperatures, and number densities are evident. Radial velocity measurements, however, show excellent agreement with predictions. The discrepancies are attributed primarily to inefficient mixing and combustion caused by the injection of excessive oxidizer along one side of the thrust chamber. Thrust and mass flow rate estimates obtained from the Rayleigh measurements show excellent agreement with the globally measured values.
Document ID
19920019232
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Zupanc, Frank J.
(NASA Lewis Research Center Cleveland, OH, United States)
Weiss, Jonathan M.
(Pennsylvania State Univ. University Park., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Subject Category
Optics
Report/Patent Number
AIAA PAPER 92-3351
E-7145
NAS 1.15:105739
NASA-TM-105739
Meeting Information
Meeting: Joint Propulsion Conference and Exhibit
Location: Nashville, TN
Country: United States
Start Date: July 6, 1992
End Date: July 8, 1992
Sponsors: ASME, AIAA, ASEE, SAE
Accession Number
92N28475
Funding Number(s)
PROJECT: RTOP 506-42-31
Distribution Limits
Public
Copyright
Public Use Permitted.
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