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- W2018479658 abstract "A multi-element rocket combustor has been designed, built, and tested to provide detailed validation data for CFD models and provide insight into the three-dimensional effects of element-to-element interaction on perfor mance and heat transfer at realistic engine operating conditions. Using gaseous hydrogen and liquid oxygen propellants with a sevenelement injector, the combustion chamber is instrumented to measure variation in heat flux both circumferentially and axially. Initial tests i ndicate that heat flux differences as small as 0.02 Btu in -1 sec -2 can be resolved. Additionally, the determination o f heat flux from temperature measurements is revisited and alternate methods of data reduction reviewed." @default.
- W2018479658 created "2016-06-24" @default.
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- W2018479658 date "2008-07-21" @default.
- W2018479658 modified "2023-09-26" @default.
- W2018479658 title "Measurement and Analysis of Heat Transfer in a Multi-Element Hydrogen/Oxygen Rocket Combustor" @default.
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- W2018479658 doi "https://doi.org/10.2514/6.2008-5031" @default.
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