Two-dimensional unsteady lift problems in supersonic flight Metadata
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- Main Title Two-dimensional unsteady lift problems in supersonic flight
- Series Title NACA Technical Reports
Author: Heaslet, Max A.Creator Type: Personal
Author: Lomax, HarvardCreator Type: Personal
Originator: Ames Aeronautical Laboratory (U.S.)Contributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Ames Aeronautical Lab
- Creation: 1947-12-05
- Content Description: The variation of pressure distribution is calculated for a two-dimensional supersonic airfoil either experiencing a sudden angle-of-attack change or entering a sharp-edge gust. From these pressure distributions the indicial lift functions applicable to unsteady lift problems are determined for two cases. Results are presented which permit the determination of maximum increment in lift coefficient attained by an unrestrained airfoil during its flight through a gust. As an application of these results, the minimum altitude for safe flight through a specific gust is calculated for a particular supersonic wing of given strength and wing loading.
- Physical Description: 9 p.
- Keyword: lift characteristics
- Keyword: unsteady lift problems
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: 93R21300
- URL: http://hdl.handle.net/2060/19930092010
- Report No.: NACA-TR-945
- Center for AeroSpace Information Number: 19930092010
- Archival Resource Key: ark:/67531/metadc60268