An Approximate Method for Calculation of the Laminar Boundary Layer with Suction for Bodies of Arbitrary Shape Metadata
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- Main Title An Approximate Method for Calculation of the Laminar Boundary Layer with Suction for Bodies of Arbitrary Shape
- Series Title NACA Technical Memorandums
- Parallel Title Ein Näherungsverfahren zur Berechnung der laminaren Grenzschicht mit Absaugung bei beliebiger Körperform
Author: Schlichting, H.Creator Type: Personal
Originator: United States. National Advisory Committee for Aeronautics.Contributor Type: Organization
Originator: Aerodynamisches Institut der Technischen HochschuleContributor Type: Organization
- Creation: 1949-03
- Content Description: From Summary: "Various ways were tried recently to decrease the friction drag of a body in a flow; they all employ influencing the boundary layer. One of them consists in keeping the boundary layer Laminar by suction; promising tests have been carried out. Since for large Reynolds numbers the friction drag of the laminar boundary layer is much lower than that of the turbulent boundary layer, a considerable saving in drag results from keeping the boundary layer laminar, even with the blower power required for suction taken into account."
- Physical Description: 85 p. : ill.
- Keyword: aerodynamics
- Keyword: boundary layer suction
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
- URL: http://hdl.handle.net/2060/20050031104
- Report No.: NACA-TM-1216
- Center for AeroSpace Information Number: 20050031104
- Archival Resource Key: ark:/67531/metadc64833