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- W2313357112 abstract "Ramjet induced compressed air to a secondary combustor and mixed with fuel. High thrust was needed to overcome air drug, therefore the diameter of nozzle throat must be large. The flow speed in the secondary combustor was higher than 200 m/s. The residue time in the secondary combustor was shorter than 10 ms, and the mixture gas burned at very short time. To increase combustion efficiency, the reaction rates of metal particles and mixture gas should be high, however mean temperature of mixture gas was 700 K and was impossible to ignite at short time. Local temperature of mixture gas in recirculation zone of the secondary combustor was an important factor to increase reaction rate of mixture gas. The surrounding gas temperature of solid particles in the recirculation zone was higher than mean temperature, and this was possible to become the ignition point. The combustion efficiency of the connected-pipe ducted rocket with the solid particles over 20 parts was larger than that without solid particles." @default.
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- W2313357112 date "2008-07-21" @default.
- W2313357112 modified "2023-09-26" @default.
- W2313357112 title "Mass Transfer in the Recirculation Zone of Ducted Rocket" @default.
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- W2313357112 doi "https://doi.org/10.2514/6.2008-4892" @default.
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