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The Lift Distribution of Swept-Back WingsTwo procedures for calculating the lift distribution along the span are given in which a better account is taken of the distribution of circulation over te area than in the Prandtl lifting-line theory. The methods are also applicable to wing sweepback. Calculated results for the two methods were in agreement.
Document ID
20030064148
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Weissinger, J. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 1947
Publication Information
Publication: Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters
Issue: 1553
Subject Category
Aerodynamics
Report/Patent Number
NACA-TM-1120
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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