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Comparison of predicted and experimental wall temperatures for a cylindrical ejector exhaust nozzle operated with a turbojet gas generator

Author: Arthur Lieberman; United States. National Aeronautics and Space Administration.; Lewis Research Center.
Publisher: Washington : National Aeronautics and Space Administration, 1971.
Series: NASA technical note, D-6465.
Edition/Format:   eBook : Document : National government publication : EnglishView all editions and formats
Summary:
The shroud wall temperatures during operation with and without an afterburner are predicted analytically by using a wall heat balance of hot gas radiation, coolant convection, internal and external radiation, and external free convection. The Hatch-Papell film-cooling correlation predicts an adiabatic wall temperature which is used as the driving temperature for the coolant heat transfer. Ejectors with nozzle area  Read more...
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Additional Physical Format: Online version:
Lieberman, Arthur.
Comparison of predicted and experimental wall temperatures for a cylindrical ejector exhaust nozzle operated with a turbojet gas generator.
Washington : National Aeronautics and Space Administration, 1971
(OCoLC)761397138
Material Type: Document, Government publication, National government publication, Internet resource
Document Type: Internet Resource, Computer File
All Authors / Contributors: Arthur Lieberman; United States. National Aeronautics and Space Administration.; Lewis Research Center.
OCLC Number: 49231757
Notes: N71-32156.
Prepared by Lewis Research Center.
Description: 1 online resource (56 pages) : illustrations.
Series Title: NASA technical note, D-6465.
Responsibility: Arthur Lieberman.

Abstract:

The shroud wall temperatures during operation with and without an afterburner are predicted analytically by using a wall heat balance of hot gas radiation, coolant convection, internal and external radiation, and external free convection. The Hatch-Papell film-cooling correlation predicts an adiabatic wall temperature which is used as the driving temperature for the coolant heat transfer. Ejectors with nozzle area ratios from 1.65 to 2. 75 and ejector length to primary diameter ratios from 1.63 to 1.95 were tested. Tests were conducted at nozzle pressure ratios ranging from 2.0 to 6.3, primary total temperatures from 861 to 1939 K (1550 [degree] to 3490 [degree] R), and corrected secondary weight-flow ratios from 0.027 to 0.088. The predictions yielded reasonably good results throughout the range of conditions tested.

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