Accession Number : ADA306740
Title : Experimental Evaluation of Six Ablative-Material Thrust Chambers As Components of Storable-Propellant Rocket Engines.
Descriptive Note : Technical note,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
Personal Author(s) : Shinn, Arthur M., Jr
PDF Url : ADA306740
Report Date : JUN 1967
Pagination or Media Count : 45
Abstract : Six ablative-material thrust chambers were tested as components of storable-propellant (nitrogen tetroxide N2O4 and a 50-50 blend of unsymmetrical dimethyl hydrazine with hydrazine N2H4) rocket engines. The nominal initial nozzle-throat diameters were 7.82 inches (19.8 cm). Engine operating conditions were held constant at a chamber pressure of 100 psia (689 kN/sq meters) and an oxidant-to-fuel ratio of 2.0. The six ablative-material thrust chambers provided both material and geometry variables. p4
Descriptors : *ROCKET ENGINES, *THRUST CHAMBERS, *ABLATIVE MATERIALS, *STORABLE ROCKET PROPELLANTS, TEST AND EVALUATION, DIMETHYLHYDRAZINES, RESISTANCE, ELASTOMERS, GRAPHITE, COOLING, EROSION, PURITY, FABRICS, GEOMETRY, ADDITIVES, SILICA GLASS, PHENOLIC PLASTICS, FIBER REINFORCEMENT.
Subject Categories : Liquid Propellant Rocket Engines
Elastomers and Rubber
Distribution Statement : APPROVED FOR PUBLIC RELEASE