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- W2096319510 abstract "Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air." @default.
- W2096319510 created "2016-06-24" @default.
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- W2096319510 date "1958-03-06" @default.
- W2096319510 modified "2023-09-27" @default.
- W2096319510 title "Investigation of a High-flow Transonic-compressor Inlet Stage Having a Hub-tip Radius Ratio of 0.35" @default.
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- W2096319510 hasPublicationYear "1958" @default.
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