Accession Number : AD0830916

Title :   LIQUID OXYGEN PRESSURE DROP FLOW TEST,

Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Personal Author(s) : Murphy, R. B.

Report Date : 22 JAN 1959

Pagination or Media Count : 43

Abstract : The available NPSH at the oxidizer turbo-pump inlets, particularly during sea level static firings, is such that it was deemed necessary to investigate the hydro-dynamic characteristics of the low pressure oxidizer plumbing for the XSM-65B Missile to determine if any marginal or detrimental conditions exist in the system. The object was to determine the steady state flow pressure losses in the low pressure oxidizer plumbing. (Author)

Descriptors :   (*LIQUID ROCKET OXIDIZERS, PROPELLANT CONTROL), (*PROPELLANT CONTROL, PRESSURIZATION), SURFACE TO SURFACE MISSILES, SIMULATION, PIPES, CAVITATION, SUSTAINER ENGINES, TURBOPUMPS, TEST METHODS, INSTRUMENTATION, PERFORMANCE(ENGINEERING), MODIFICATION KITS, SEQUENCES(MATHEMATICS), SKIN FRICTION, PRESSURE GAGES.

Subject Categories : Surface-launched Guided Missiles
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE