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Laser Transmission Measurements of Soot Extinction Coefficients in the Exhaust Plume of the X-34 60k-lb Thrust Fastrac Rocket EngineA four-channel laser transmissometer has been used to probe the soot content of the exhaust plume of the X-34 60k-lb thrust Fastrac rocket engine at NASA's Marshall Space Flight Center. The transmission measurements were made at an axial location about equal 1.65 nozzle diameters from the exit plane and are interpreted in terms of homogeneous radial zones to yield extinction coefficients from 0.5-8.4 per meter. The corresponding soot mass density, spatially averaged over the plume cross section, is, for Rayleigh particles, approximately equal to 0.7 micrograms/cubic cm and alternative particle distributions are briefly considered. Absolute plume radiance at the laser wavelength (515 nm) is estimated from the data at approximately equal to 2.200 K equivalent blackbody temperature, and temporal correlations in emission from several spatial locations are noted.
Document ID
20000080356
Acquisition Source
Headquarters
Document Type
Technical Publication (TP)
Authors
Dobson, C. C. (NASA Marshall Space Flight Center Huntsville, AL United States)
Eskridge, R. H. (NASA Marshall Space Flight Center Huntsville, AL United States)
Lee, M. H. (NASA Marshall Space Flight Center Huntsville, AL United States)
Date Acquired
August 19, 2013
Publication Date
March 1, 2000
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.60:210075
M-972
NASA/TP-2000-210075
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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