Investigation of Downwash, Sidewash, and Mach Number Distribution Behind a Rectangular Wing at a Mach Number of 2.41 Metadata
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Title
- Main Title Investigation of Downwash, Sidewash, and Mach Number Distribution Behind a Rectangular Wing at a Mach Number of 2.41
- Series Title NACA Technical Reports
Creator
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Author: Adamson, DavidCreator Type: Personal
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Author: Boatright, William B.Creator Type: Personal
Contributor
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Originator: Langley Aeronautical LaboratoryContributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Langley Aeronautical Lab
Date
- Creation: 1950-09-14
Language
- English
Description
- Content Description: "An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight" (p. 1).
- Physical Description: 115 p. : ill.
Subject
- Keyword: aircraft wings
- Keyword: flow fields
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: 93R21618
- URL: http://hdl.handle.net/2060/19930092328
- Report No.: NACA-TR-1340
- Center for AeroSpace Information Number: 19930092328
- Archival Resource Key: ark:/67531/metadc60746