Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle Metadata
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- Main Title Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle
- Series Title NACA Research Memorandums
Author: Dietz, Robert O., Jr.Creator Type: Personal
Author: Krebs, Richard P.Creator Type: Personal
Originator: Lewis Flight Propulsion LaboratoryContributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab
- Creation: 1949-05-16
- Content Description: Report presenting the results of an analytical investigation, which demonstrated that the inlet of a turbojet engine can be protected from ice accretions by bleeding hot gases from other locations within the engine to the inlet without undue loss in thrust. Results regarding the bleedback requirements, engine performance, effect of nozzle area, mixing efficiency, and seriousness of thrust losses are provided.
- Physical Description:  p.
- Keyword: turbojet engines
- Keyword: ice prevention
- Keyword: gas bleedback
Name: National Advisory Committee for Aeronautics CollectionCode: NACA
Name: Technical Report Archive and Image LibraryCode: TRAIL
Name: UNT Libraries Government Documents DepartmentCode: UNTGD
- Rights Access: public
- Rights License: pd
- Rights Statement: No Copyright, Unclassified, Unlimited, Publicly available
- Accession or Local Control No: 93R15266
- URL: http://hdl.handle.net/2060/19930085976
- Report No.: NACA-RM-E9B23
- Center for AeroSpace Information Number: 19930085976
- Archival Resource Key: ark:/67531/metadc58308