Experimental Investigation of Heat Transfer in a Subscale Liquid Rocket Engine
Author:
Affiliation:
1. ONERA—The French Aerospace Lab, 91761 Palaiseau, France
2. French National Center for Scientific Research, 31400 Toulouse, France
3. National Centre for Space Studies, 75012 Paris Cedex, France
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.B36928
Reference24 articles.
1. Atomization and Breakup of Cryogenic Propellants Under High-Pressure Subcritical and Supercritical Conditions
2. Heat transfer characteristics of H2/O2-combustion chambers
3. Benchmark Wall Heat Flux Data for a GO2/GH2 Single Element Combustor
4. Heat Flux and Pressure Profiles in an Oxygen/Hydrogen Multielement Rocket Combustor
5. Heat Flux Measurements for a GO2/GH2 Single-Element, Shear Injector
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