Comparison of theoretical and experimental stresses in an F8U-3 airplane wnig loaded in torison
By: Donald Bruce Messerschmidt
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1967
Place of publication: Monterey, Calif
Language: eng
Number of pages: 70
Description: 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.
Notes: Thesis Advisor(s): Kahr, Charles H.

"December 1967."

Description based on title screen as viewed on December 3, 2007.

Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, December 1967.

Includes bibliographical references (p. 59)

"New limitation change: Approved for public release, distribution unlimited. Authority: ST-A USNPS LTR, 1 Oct 71."

Also available in print.

Mode of access: World Wide Web.

System requirements: Adobe Acrobat Reader.

US Marine Corps (USMC) author.

US Marine Corps (USMC) author.

upgraded: 12/20/07 dk