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Calculations, and comparison with an ideal minimum, of trimmed drag for conventional and canard configurations having various levels of static stabilityClassical drag equations were used to calculate total and induced drag and ratios of stabilizer lift to wing lift for a variety of conventional and canard configurations. The Flight efficiencies of such configurations that are trimmed in pitch and have various values of static margin are evaluated. Classical calculation methods are compared with more modern lifting surface theory.
Document ID
19770017118
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Mclaughlin, M. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
L-11016
NASA-TN-D-8391
Accession Number
77N24062
Funding Number(s)
PROJECT: RTOP 512-53-01-12
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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