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.

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.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1967
Accession Number
ADA306739

Entities

People

  • Donald A. Peterson

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ablative Materials
  • Boundary Layer
  • Combustion
  • Combustion Chambers
  • Composite Materials
  • Corrosion Resistance
  • Equations
  • Erosion Resistance
  • Flow Rate
  • Material Degradation Processes
  • Materials
  • Materials Processing
  • Measurement
  • Resins
  • Rocket Engines
  • Rocket Oxidizers
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Rocket Propulsion.