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Title:
Survey of recent Al2O3 droplet size data in solid rocket chambers, nozzles, and plumes
Authors:
Salita, Mark
Affiliation:
AA(Analytical Methods, Inc., Bellevue, WA.)
Publication:
In Johns Hopkins Univ., The 31st JANNAF Combustion Subcommittee Meeting, Volume 1 p 1-18 (SEE N95-31194 11-28)
Publication Date:
10/1994
Category:
Spacecraft Propulsion and Power
Origin:
STI
NASA/STI Keywords:
Aluminum Oxides, Drop Size, Drops (Liquids), Plumes, Propellant Combustion, Rocket Nozzles, Surveys, Thrust Chambers, Burning Time, Diameters, Mass Distribution, Particle Size Distribution, Solid Propellant Rocket Engines, Standard Deviation
Bibliographic Code:
1994jann....1....1S

Abstract

The size distribution of Al2O3 droplets in a solid propellant rocket is very different in the chamber, nozzle, and plume, primarily due to breakup and collision/coalescence in the nozzle. This paper attempts to summarize, evaluate, and relate the results of 19 recent experimental and analytical studies of droplet size in order to construct a unified model of droplet size evolution from the chamber through the nozzle and into the plume. It is believed that the distribution of droplet mass in the chamber is bimodal log-normal, with 1 micron smoke comprising about 80% of the mass and 50-100 micron caps comprising the remaining 20%. During passage through the nozzle, the caps shatter to product droplets whose diameters are about 10% of the caps but still 10 times those of smoke, while all but 1-2% of the smoke mass collides and coalesces with the shatter products to generate an essentially monomodal mass distribution at the nozzle exit whose D43 agrees with Hermsen's correlation and whose standard deviation alpha approximately or equal to 0.13 is smaller than both the chamber smoke (alpha approximately or equal to 0.40) or caps (alpha approximately or equal to 0.20).
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