Accession Number : AD0647309

Title :   HIGH TEMPERATURE RESISTANT MATERIALS FOR MISSILE PROPULSION SYSTEMS.

Descriptive Note : Summary rept., 30 Jun 65-30 Jun 66,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Caum,D. M. ; Hartmann,B. T. ; Koubek,F. J.

Report Date : 27 DEC 1966

Pagination or Media Count : 51

Abstract : A temperature prediction program showed agreement to within 10 to 25% of experimental internal temperature for three ablators tested in the oxy-acetylene burner. However, if alpha (effective thermal diffusivity) is not obtained under steady-state ablation conditions, the agreement could be several hundred per cent in error. The alpha-rod test technique was found to be useful for ablators with widely varying properties. The NOL oxy-acetylene panel test was accepted and published as a tentative ASTM method. (Author)

Descriptors :   (*COMPOSITE MATERIALS, ABLATION), (*HEAT SHIELDS, COMPOSITE MATERIALS), (*HIGH TEMPERATURE, MATERIALS), (*ROCKET ENGINES, HEAT RESISTANT MATERIALS), HEAT RESISTANT PLASTICS, PHENOLIC PLASTICS, FOAM, CERAMIC MATERIALS, LAMINATED PLASTICS, SYNTHETIC RUBBER, ASBESTOS, GLASS TEXTILES, NYLON, EPOXY RESINS

Subject Categories : Laminates and Composite Materials
      Air Condition, Heating, Lighting & Ventilating
      Test Facilities, Equipment and Methods
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE