Graphite Rocket Nozzle Erosion Rate Reduction by Boundary-Layer Control Using Ablative Materials
Author:
Affiliation:
1. Dept. of Mechanical and Nuclear Engineering, The Pennsylvania State Univ.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2007-782
Reference28 articles.
1. Burning carbon particles in the presence of water vapor
2. Ignition, combustion, and extinction of carbon particles
3. The gasification of carbon by carbon dioxide at high temperatures and pressures
4. Comparative studies of the attack of pyrolytic and isotropic graphite by atomic and molecular oxygen at high temperatures.
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1. High-Temperature Oxidation Kinetics of Tungsten-Water Reaction with Hydrogen Inhibition;Journal of Propulsion and Power;2011-09
2. Mitigation of Graphite Nozzle Erosion by Boundary-Layer Control in Solid Propellant Rocket Motors;Journal of Propulsion and Power;2009-09
3. Kinetic Mechanisms of High Temperature Tungsten Oxidation: Experimental Evaluation with Modeling;45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2009-08-02
4. High-Temperature Heterogeneous Reaction Kinetics of Tungsten Oxidation by CO2, CO, and O2;Journal of Propulsion and Power;2009-03
5. Chemical Erosion of Graphite Nozzle Material in Solid Rocket Motors;43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2007-07-08
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