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Ignition Delay Experiments with Small-scale Rocket Engine at Simulated Altitude Conditions Using Various Fuels with Nitric Acid Oxidants / Dezso J. LadanyiIgnition delay determinations of several fuels with nitric oxidants were made at simulated altitude conditions utilizing a small-scale rocket engine of approximately 50 pounds thrust. Included in the fuels were aniline, hydrazine hydrate, furfuryl alcohol, furfuryl mercaptan, turpentine, and mixtures of triethylamine with mixed xylidines and diallyaniline. Red fuming, white fuming, and anhydrous nitric acids were used with and without additives. A diallylaniline - triethylamine mixture and a red fuming nitric acid analyzing 3.5 percent water and 16 percent NO2 by weight was found to have a wide temperature-pressure ignition range, yielding average delays from 13 milliseconds at 110 degrees F to 55 milliseconds at -95 degrees F regardless of the initial ambient pressure that ranged from sea-level pressure altitude of 94,000 feet.
Document ID
19930086908
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Ladanyi, Dezso J
Date Acquired
August 16, 2013
Publication Date
January 9, 1952
Report/Patent Number
NACA-RM-E51J01
Accession Number
93R16198
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
TRIETHYLAMINE
FURFURYL ALCOHOL
ENGINE STARTING
ANILINE
NITRIC ACID
ALTITUDE TEST CHAMBERS - ENGINES - LFPL
DIALLYLANILINE
XYLIDINE
HYDRAZINE HYDRATE
ENGINES, ROCKET - ALTITUDE TESTS
FURFURYL MERCAPTAN
PROPELLANTS - IGNITION
TURPENTINE

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