Accession Number : AD0372023

Title :   THE EXPERIMENTAL EVALUATION OFZ(HYBALINE B3.)Z

Descriptive Note : Final rept.,

Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF

Personal Author(s) : Nidiffer,Kenneth E.

Report Date : NOV 1965

Pagination or Media Count : 43

Abstract : Hybaline B3 was subjected to 87 test firings in a nominal 100-lb thrust uncooled rocket engine at a chamber pressure of 300 psia. Thirty-seven tests were made with N2O4, 43 with 90 wt % H2O2 and the remainder with 98 wt % H2O2. Twenty-five tests were performed with H2O4 at 500-lb thrust and 1000-psia chamber pressure. Delivered performance with both oxidizers was low in the region of maximum theoretical impulse; however, performance efficiencies significantly increased at weight O/F ratios where combustion temperature was near or above the melting point of beryllium oxide. Thermal stability data are given, as is compatibility information. (Author)

Descriptors :   (*LIQUID ROCKET FUELS, SPECIFIC IMPULSE), (*LIQUID ROCKET PROPELLANTS, SPECIFIC IMPULSE), LIQUID ROCKET OXIDIZERS, HYPERGOLIC ROCKET PROPELLANTS, COMBUSTION, LIQUID PROPELLANT ROCKET ENGINES, COMBUSTION CHAMBERS, COMBUSTION CHAMBER LINERS, FUEL INJECTORS, THRUST, INTERIOR BALLISTICS, MIXTURES, FLUID FLOW, THERMAL STABILITY, SAFETY, COMPATIBILITY (U) (*BERYLLIUM COMPOUNDS), COMPLEX COMPOUNDS, AMINES, BOROHYDRIDES, ALUMINUM COMPOUNDS, HYDROGEN PEROXIDE, NITROGEN COMPOUNDS, TETROXIDES

Subject Categories : Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE