Results of wind-tunnel tests on airfoil designed according to methods published in October 25, 1927, issue of magazine, part of which is reprinted here; approximate formula is derived for airfoil profile drag applying to best smooth fair airfoils of modern design at full-flight scale; by manipulation of basic section, changing thickness or curvature of median line or both, infinite number of sections may be obtained which are affinal; layout data for basis section.
An approximate expression for airfoil profile drag
Aviation
Aviation ; 27 , n 12
1929
2 pages
3 Figs.
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
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