Langley Memoir on Mechanical Flight, Parts I and II: Smithsonian Contributions to Knowledge, Volume 27 Number 3, Publication 1948, 1911Langley, S. P. (Samuel Pierpont)
History
Langley Memoir on Mechanical Flight, Parts I and II: Smithsonian Contributions to Knowledge, Volume 27 Number 3, Publication 1948, 1911
Langley, S. P. (Samuel Pierpont)
Aeronautics; Flight
To these main ribs were attached, in the manner later described,
the 10 cross-ribs, to which the cloth cover was attached. The 8
intermediate cross-ribs have already been described in connection
with the tests. The cross-ribs at the end of the wings, upon which
greater lateral strains would come from the stretching of the cloth,
were made of the larger cross-section shown in Fig. 8 of Plate 66.
Additional longitudinal stiffness was provided by gluing a strip
2 mm. thick between the upper and lower halves, as shown in the
section. These end ribs, as well as those next to the ends, had
small blocks glued into them where they were crossed by the diagonal
braces, in addition to the small partitions 1 mm. thick, which were
glued into the ribs every 3 inches to prevent crushing, and the
blocks 2.5 and 3 inches long respectively, where they were attached
to the front rib and to the mid-rib. At the extreme rear edge of the
wing the cross-ribs were attached to the small “D”-rib, which served
to hold the ribs at equal distances and to keep the cloth cover
stretched tight. This “D”-rib, as shown in Plate 66, Fig. 3, had
semi-circular walls 4 mm. thick, 21 mm. in diameter, to the edge of
which was glued a flat strip 3 mm. thick. [p205]
As originally designed the wings had a curve of only 1 in 18, the
main front rib forming the leading edge of the wing. Later, however,
it seemed desirable to “quicken” the curve and at the same time give
the wing a sharper leading edge. This was accomplished by attaching
to the front rib, at the points where the cross-ribs joined it,
properly curved wooden pieces of the form shown in Plate 66, Fig. 10,
over which the cloth cover of the wing was stretched. The curve of
the wing after the addition of this extension is shown in Plate 66,
Fig. 4, and was a curve having a rise of approximately 1 in 12, with
the highest point .25 from the front end.
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