Effect of Variable-position Inlet Guide Vanes and Interstage Bleed on Compressor Performance of a High-pressure-ratio Turbojet Engine PDF Download
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Author: S.C. Huntley
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Category :
Languages : en
Pages : 26
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Author: S.C. Huntley
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Category :
Languages : en
Pages : 26
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Author: Ray E. Budinger
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Category : Airplanes
Languages : en
Pages : 48
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Author: United States. National Aeronautics and Space Administration
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Category : Aeronautics
Languages : en
Pages : 448
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Author: United States. National Advisory Committee for Aeronautics
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Category : Aeronautics
Languages : en
Pages : 860
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Category : Aeronautics
Languages : en
Pages : 296
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Category : Aerodynamics
Languages : en
Pages : 464
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Author: United States. National Aeronautics and Space Administration
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Category :
Languages : en
Pages :
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Category : Aeronautics
Languages : en
Pages : 494
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Author: United States. Superintendent of Documents
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Category : Government publications
Languages : en
Pages : 1812
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Author: Stanley L. Koutz
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Category : Airplanes
Languages : en
Pages : 52
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In general, with a turbojet engine operating at constant engine speed, bleeding gas from the tail pipe at constant tail-pipe-nozzle area and reduced turbine-inlet temperature caused 2.5 to 4 times as great a loss in thrust as bleeding gas at constant turbine-inlet temperature and reduced tail-pipe-nozzle area.
