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- W1964190947 abstract "The application of a modified sodium-line reversal technique to the measurement of combustion temperature at several stations within an open tube rocket combustor was investigated. The measurement technique, experimental apparatus, and results are described and discussed. The effect of oxidant-fuel ratio on axial temperature distribution for a single two-on-one impingement type injector utilizing liquid oxygen and alcohol as propellants was evaluated. The experimental results indicate tha t the technique may be successfully applied to the study of combustion reaction t ime in rocket engines." @default.
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- W1964190947 date "1953-07-01" @default.
- W1964190947 modified "2023-09-26" @default.
- W1964190947 title "A Modified Sodium-Line Reversal Technique for the Measurement of Combustion Temperatures in Rocket Engines" @default.
- W1964190947 cites W2077950973 @default.
- W1964190947 cites W2143582434 @default.
- W1964190947 doi "https://doi.org/10.2514/8.4606" @default.
- W1964190947 hasPublicationYear "1953" @default.
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