Comparison of theoretical and experimental stresses in an F8U-3 airplane wing loaded in torsion
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Authors
Messerschmidt, Donald Bruce
Subjects
Matrix-force method
Strain energy analysis
Swept-wing structural analysis
Strain energy analysis
Swept-wing structural analysis
Advisors
Kahr, Charles H.
Date of Issue
1967-12
Date
December 1967
Publisher
Monterey, California. U.S. Naval Postgraduate School
Language
en_US
Abstract
The stresses near the root of an F8U-3 airplane wing loaded in torsion found using the matrix-force method of analysis . The wing was represented by a simplified, idealized model consisting of axial-load carrying flange bars and shear carrying cover plates. The theoretical stresses in the idealized model were found by using the IBM 360/67 computer to solve for the redundant loads. These stresses show favorable comparison with the experimental stresses determined from strain gages mounted on the cover skin of the wing. This study shows that the matrix method is applicable to thick-skinned wings
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautics
Organization
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funder
Format
70 p.: ill.
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.