Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000 Metadata
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- Main Title Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000
- Series Title NACA Research Memorandums
Author: Salmi, Reino J.Creator Type: Personal
Author: Conner, D. WilliamCreator Type: Personal
Author: Graham, Robert R.Creator Type: Personal
Originator: Langley Aeronautical LaboratoryContributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Langley Aeronautical Lab
- Creation: 1947-06-10
- Content Description: Wind-tunnel investigations were made in pitch and yaw with and without split flaps. Presence of the fuselage had negligible effect on values of maximum lift coefficient and slope of lift curve, but caused a destabilizing shift in the rate of change of pitching moment with lift. Effects of fuselage position on drag characteristics were small for wings without flaps, but were appreciable when split flaps were on.
- Physical Description:  p. : ill.
- Keyword: aerodynamics
- Keyword: split flaps
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: 93R19636
- URL: http://hdl.handle.net/2060/19930090346
- Report No.: NACA-RM-L7E13
- Center for AeroSpace Information Number: 19930090346
- Archival Resource Key: ark:/67531/metadc64565