Accession Number : AD0475759
Title : CASTABLE CARBON FOR NOZZLE APPLICATIONS.
Descriptive Note : Quarterly progress rept. no. 4, 1 Dec 64-1 Mar 65,
Corporate Author : ATLANTIC RESEARCH CORP ALEXANDRIA VA
Personal Author(s) : Batchelor, James D.
Report Date : MAR 1965
Pagination or Media Count : 23
Abstract : An investigation is reported of a unique castable carbon material developed for rocket nozzle applications. The second and third subscale nozzles (for the 5,000 pound thrust motor) were motor tested at the Air Force Rocket Propulsion Laboratory. In the second subscale test, the exit cone was burned off the nozzle after 43 seconds following excessive erosion of the cast carbon immediately aft of the graphite throat insert. The third subscale nozzle, which consisted entirely of cast carbon in a steel housing, performed acceptably. Throat performance was good but uneven erosion aft of the throat produced local gouging in the exit cone. Emphasis will be placed on improved material for the throat and initial expansion area. (Author)
Descriptors : , (*ROCKET NOZZLES, CARBON), MANUFACTURING, CASTINGS, THRUST, PERFORMANCE(ENGINEERING), EXPERIMENTAL DESIGN, CAPTIVE TESTS, NOZZLE INSERTS, NOZZLE THROATS, SOLID PROPELLANT ROCKET ENGINES, BURNTHROUGH, EROSION, GRAPHITE, TEMPERATURE, EXHAUST NOZZLES.
Subject Categories : SOLID PROPELLANT ROCKET ENGINES
Distribution Statement : APPROVED FOR PUBLIC RELEASE