Accession Number:

AD0662679

Title:

HIGH TEMPERATURE RESISTANT MATERIALS FOR MISSILE PROPULSION SYSTEMS

Descriptive Note:

Summary rept., 30 Jun 1966-30 Jun 1967

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

Report Date:

1967-10-09

Pagination or Media Count:

29.0

Abstract:

Steady state ablation was reached in oxy-acetylene burner tests on extra long specimens of phenolic asbestos. Also tested and analyzed were two densities of foamed silica. Calculation of alpha vs. temperature from experimental data was programmed for a digital computer. A detailed study of the NOL transient calorimeter was made. Generally, the existence of a linear temperature rise on the back face is sufficient evidence that errors are negligible.

Subject Categories:

  • Laminates and Composite Materials
  • Air Conditioning, Heating, Lighting and Ventilating
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE