Span-Load Distribution as a Factor in Stability in Roll (1932)
NASA Technical Reports Server (NTRS) · leaf 7
etail in reference 2. Figure 2 shows the N. A. C. A. 84 model washed out The general design of the two semispan wing models 15° about an axis coincident with the leading edge. and the locations of the test orifices are shown in In order to set the twist the long bolts were loosened Figure 3, and… … opprox. 3/16" K' k k K- k- ... ^ ^ ^. ^1 Tip section N.A.C.A. f^2 /.30Z- 6.75Z- Root section N.A.C.A. 84 N.A.C.A. 86 Figure 3.—Orifice locations on semispan twistable wing models nated the N. A. C. A. 84, is of constant profile and scribed on the leading edge of the model coincided with thickness…
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