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THE liquid propellant combustion device has always presented design and development risks because of the required harsh operating thermal environment, usually at high pressures, and because of the secondary goals of small packaging, light weight, high performance efficiency, and low cost.
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Journal of Fluid Mechanics, Physics of Fluids, New York, Proceedings of the Combustion Institute, United States, Jet Propulsion, Canoga Park, Begell House, Chemical Propulsion Information Agency, Senior Member, Mashinostroenie Pub, Final Report, Final Rept, International Journal of Multiphase Flow, Centre National, Chemical Engineering Science, Department of Mechanical Engineering, Marshall Space Flight Center, University Park, Aerojet General Corp, Associate Fellow, Cambridge Univ, European Symposium, Pennsylvania State Univ, Axial Distance From Chamber Throat
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