Accession Number : ADA306739
Title : Experimental Evaluation of High-Purity-Silica Reinforced Ablative Composites As Nozzle Sections of 7.8-Inch-(19.8 CM) Diameter Throat Storable-Propellant Rocket Engine.
Descriptive Note : Memorandum rept.,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
Personal Author(s) : Peterson, Donald A.
PDF Url : ADA306739
Report Date : JUN 1967
Pagination or Media Count : 28
Abstract : Eleven high-purity-silica reinforced ablative materials were evaluated as nozzle sections of a storable propellant (nitrogen tetroxide and a blend of 50-percent unsymmetrical dimethylhydrazine and 50-percent hydrazine) rocket engine. Testing was performed at an oxidant-to-fuel ratio of 2. 0, a chamber pressure of 100 psia (689 kN/sq meters) and an initial throat diameter of 7. 82 inches (19. 8 cm). Both oxidant-to-fuel ratio and chamber pressure were maintained constant during the test firing at an equivalent pressure altitude of 1.60 psia (11. 05 kN/sq meters). Erosion rates, char information, and a discussion of the effect on erosion of some major material and processing variables are presented.
Descriptors : *EXPERIMENTAL DATA, *PURITY, *NOZZLE THROATS, *SILICA GLASS, *ABLATIVE MATERIALS, *REINFORCED PLASTICS, *STORABLE ROCKET PROPELLANTS, TEST AND EVALUATION, HYDRAZINES, DIMETHYLHYDRAZINES, VARIABLES, EROSION, PRESSURE, NITROGEN OXIDES, ALTITUDE, ROCKET ENGINES, CHAMBERS, CHARRING, TETROXIDES.
Subject Categories : Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE