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A method, based on the elastic theory for plate buckling and test results for 24S-T aluminum-alloy Z-stiffened panels, is shown for calculating the compressive strength of Z-stiffened panels that develop local instability. This method can be used to calculate the critical compressive stress above, as well as within, the elastic range. For stresses above three-fourths the compressive yield stress the method can be used for the approximate determination of the average compressive stress at maximum load.
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A Method of calculating the compressive strength of Z-stiffened panels that develop local instability
1947, National Advisory Committee for Aeronautics
in English
1680156101 9781680156102
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Edition Notes
"November 1947."
NACA TN No. 1482.
Includes bibliographical references.
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