Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap Metadata
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Title
- Main Title Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap
- Series Title NACA Research Memorandums
Creator
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Author: Czarnecki, K. R.Creator Type: Personal
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Author: Mueller, James N.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: 1951-01-02
Language
- English
Description
- Content Description: Report presenting an investigation at supersonic speeds of some of the factors affecting the flow over a rectangular wing with a symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. The main purpose is to obtain more information on which to base the design of supersonic controls. Results regarding the effect of Mach number, effect of wing thickness, effect of fixing transition, effect of sealing the hinge gap, effect of model surface condition and asymmetry, and shock boundary-layer interaction are provided.
- Physical Description: 111 p. : ill.
Subject
- Keyword: supersonic speeds
- Keyword: aircraft wings
- Keyword: aerodynamics
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: 93R15917
- URL: http://hdl.handle.net/2060/19930086627
- Report No.: NACA-RM-L50J18
- Center for AeroSpace Information Number: 19930086627
- Archival Resource Key: ark:/67531/metadc58826