Comparison of experimental stresses and deflections with those predicted by a strain energy method for an F8U-3 wing loaded in torsion
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Authors
Holgren, Marvin A.
Comfort, Clayton L.
Subjects
Advisors
Date of Issue
1963
Date
1963
Publisher
Monterey, California: U.S. Naval Postgraduate School
Language
en_US
Abstract
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.
Type
Thesis
Description
Series/Report No
Department
Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
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.