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The Minimum Induced Drag of AerofoilsEquations are derived to demonstrate which distribution of lifting elements result in a minimum amount of aerodynamic drag. The lifting elements were arranged (1) in one line, (2) parallel lying in a transverse plane, and (3) in any direction in a transverse plane. It was shown that the distribution of lift which causes the least drag is reduced to the solution of the problem for systems of airfoils which are situated in a plane perpendicular to the direction of flight.
Document ID
19800006779
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Report
Authors
Munk, M. M. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
August 10, 2013
Publication Date
December 1, 1979
Publication Information
Publication: NASA. Ames Res. Center Classical Aerodyn. Theory
Subject Category
Aerodynamics
Report/Patent Number
NACA-TR-121
Accession Number
80N15038
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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