Comparison of experimental stresses and deflections with those predicted by a strain energy method for an F8U-3 wing loaded in torsion
Holgren, Marvin A.
Comfort, Clayton L.
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The stress level in the milled skin at the root of a tapered, multicell swept wing is predicted by means of a matrix-force method. The solution is achieved by minimizing the internal strain energy, and the results compared with experimental tests. A single loading, consisting of a nose-up couple, is applied to each tip rib. The loading is transferred from the tip rib to an idealized structure by means of simple torsion theory. The idealized structure represents the inboard one-half of each semi-span. Results indicate that an accurate solution of the stress distribution in the actual wing can be achieved provided that the root boundary conditions are preserved. An extension of the analysis is suggested in order to more closely define the maximum accuracy inherent in the particular matrix-force method of solution.
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