Two-dimensional chord-wise load distributions at transonic speeds Metadata
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Title
- Main Title Two-dimensional chord-wise load distributions at transonic speeds
- Series Title NACA Research Memorandums
Creator
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Author: Lindsey, Walter F.Creator Type: Personal
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Author: Dick, Richard S.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: 1952-02-18
Language
- English
Description
- Content Description: Report presenting testing on the NACA 16-009 airfoil and on eight airfoils of the NACA 6A series, which shows that the chordwise loading due to lift at a Mach number of 1.0 is insignificantly affected by thickness distribution within the range of airfoil shapes presented and only slightly affected by thickness. Results regarding the experimental loading on symmetrical airfoils, method of estimating pressure distribution, experimental loadings on cambered airfoils, and scope of method are provided.
- Physical Description: 41 p. : ill.
Subject
- Keyword: airfoils
- Keyword: aircraft loading
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: 93R16086
- URL: http://hdl.handle.net/2060/19930086796
- Report No.: NACA-RM-L51I07
- Center for AeroSpace Information Number: 19930086796
- Archival Resource Key: ark:/67531/metadc58975