Performance of external-compression bump inlet at Mach numbers of 1.5 and 2.0 Metadata
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Title
- Main Title Performance of external-compression bump inlet at Mach numbers of 1.5 and 2.0
- Series Title NACA Research Memorandums
Creator
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Author: Simon, Paul C.Creator Type: Personal
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Author: Brown, Dennis W.Creator Type: Personal
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Author: Huff, Ronald G.Creator Type: Personal
Contributor
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Originator: Lewis Flight Propulsion LaboratoryContributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab
Date
- Creation: 1957-04-24
Language
- English
Description
- Content Description: Report presenting an experimental investigation of a scale model of the forebody of a proposed supersonic fighter to determine the internal performance and configuration drag of various twin-side inlets. External-compression ramp and bump inlets with various types and combinations of boundary-layer bleed were tested. Results regarding performance charts and flow characteristics are provided.
- Physical Description: 39 p. : ill.
Subject
- Keyword: aircraft drag
- Keyword: aircraft inlets
Collection
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Name: National Advisory Committee for Aeronautics CollectionCode: NACA
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Name: Technical Report Archive and Image LibraryCode: TRAIL
Institution
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Name: UNT Libraries Government Documents DepartmentCode: UNTGD
Rights
- Rights Access: public
- Rights License: pd
- Rights Statement: No Copyright, Unclassified, Unlimited, Publicly available
Resource Type
- Report
Format
- Text
Identifier
- Accession or Local Control No: 93R18914
- URL: http://hdl.handle.net/2060/19930089624
- Report No.: NACA-RM-E56L19
- Center for AeroSpace Information Number: 19930089624
- Archival Resource Key: ark:/67531/metadc63238