Analysis of the Ultimate Strength and Optimum Proportions of Multiweb Wing Structures Page: 17 of 35
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NACA TN 36 3
Use of Other Materials
Structures of materials other than the 7075-T6 aluminum alloy
considered can be compared with the structures represented in figure 4.
For the structure in question, the value of the structural index can be
obtained by test or computations, and the weight comparison is msae by
determining the equivalent solidity and the ratio of depth to skin
thickness by utilizing the ratios of densities and shear moduli of the
materials .
In order to obtain identical torsional stiffness in the newly
selected material and the reference material, let
bWGxtSx = GrtSrbWr
where G is the shear modulus of elasticity, subscript r refers to
reference material, and subscript x refers to other material.
Except for very thin wings, br P bWx and the ratio of the equiv-
alent depth to the skin thickness is given by
.grX Gx (22)
The equivalent solidity for a direct weight comparison is the
computed solidity modified as follows:
h =/A7) (23)
)r 'xwr
CONCLUDING REMARES
Equations have been presented which relate the maximum bending
strength of multiweb beams which fail in the local buckling mode to the
beam proportions and material properties. The experimental results,
upon which the equations are based, were also used to establish criteria
for the minimum web size required to support the covers satisfactorily.
The expressions for maximum strength have been used in a structural-
efficiency analysis which shows minimum weight as a function of the design
specifications. For multiweb wing structures, the significant weight16
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Rosen, B. Walter. Analysis of the Ultimate Strength and Optimum Proportions of Multiweb Wing Structures, report, March 1956; (https://digital.library.unt.edu/ark:/67531/metadc57902/m1/17/: accessed July 16, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.