Experimental Evaluation of Several Advanced Ablative Materials as Nozzle Sections of a Storable-Propellant Rocket Engine.
Abstract
Eighteen ablative materials were evaluated for their relative erosion resistance in test firings of 22 nozzles in a storable-propellant engine of a 1.2-inch (3.05-cm) diameter throat at a chamber pressure of 100 psia (689. 5 kN/m2). The materials investigated were the phenolic, polyimide, phenolic plus polyamide, epoxy novalac, and phenylsilane resins, reinforced with silica, quartz, and carbon-silica fibers. Quartz reinforcement was superior to silica with the three resins tested. The lower erosion rate is attributed to the higher melting temperature of quartz. Carbon-silica reinforcement exhibited the highest erosion rate. Its relatively poor performance is attributed to the rapid oxidation of the carbon. Ablatives made of phenolic resin had lower erosion rates than all other resins tested. Erosion at mixture ratios of 1.6 was greater than at mixture ratios of 2.0. Nozzle convergent entrance angle, throat radius of curvature, and source or resin supplier had no apparent effect on erosion resistance. A slight effect of fabrication technique on erosion was detected.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1968
- Accession Number
- ADA307843
Entities
People
- A. J. Pavli
Organizations
- Glenn Research Center