NASA-TN-D-8391
Calculations, and comparison with an ideal minimum, of trimmed drag for conventional and canard configurations having various levels of static stability
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Abstract:
Classical 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.
Author(s):
M.D. McLaughlin
Indexed under:
- None
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