Strength Calculations on Airplanes Page: 17 of 25
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N.A.C.A. Tcchnical Memorandum No. 341
aration of the suggested specifications might well be loft to
the committee on constructive problems in our association.
In recent times the number of light metals has boon great-
ly increased. It would be opportune to investigate their
adaptability to airplane construction in connection with the
above suggestions. The published data on their characteristics
are incomplete. It would, in any case, be desirable for our
association to undertake their investigation by having a corm-
mittee work out some plan for having these investigations
made in one or more laboratories, with special regard to the
requirements of airplane construction. The means for these
investigations could be provided from the emergency funds of
the German scientific societies.
For the strength calculations of an airplane, we could
start with the anticipated stresses with respect to speed,
banking ability and pressure distribution on the wings. This
load multiple would lie at 2.5 for slower airplanes and 3.5
for faster ones, without exceeding the maximum limit by in-
creasing the flight characteristics beyond what is now custom-
a.r y.
Attention should then be given to the selection of the
building materials, with special regard to their homogeneity
and the determination of their yield points. Their allowable
stressing should then be so chosen, with regard to the degrce
of uniformity that, at a 2.5 to 3.5-fold load, the stress16
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Baumann, A. Strength Calculations on Airplanes, report, December 1925; (https://digital.library.unt.edu/ark:/67531/metadc65144/m1/17/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.