A Method of calculating the compressive strength of Z-stiffened panels that develop local instability
By: by George L. Gallaher and Rolla B. Boughan
Contributors: Boughan, Rolla B.; United States. National Advisory Committee for Aeronautics
Series: National Advisory Committee for Aeronautics technical note -- number 1482; Technical note (United States. National Advisory Committee for Aeronautics) -- no. 1482.
Publisher: National Advisory Committee for Aeronautics
Published: 1947
Place of publication: Washington, D.C
Language: eng
Number of pages: 15
ISBN-13: 9781680156102
Subjects: Plates (Engineering); Strains and stresses; Buckling (Mechanics); Mathematical analysis; Plaques (Ingénierie); Contraintes (Mécanique); Flambage (Résistance des matériaux); Analyse mathématique; Stress; Strain; Warping; Buckling
Other titles: Technical Report Archive & Image Library (TRAIL)
Description: 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.
Notes: "November 1947."

NACA TN No. 1482.

Includes bibliographical references.