NDLI: Buckling behavior of rene 41 tubular panels for a hypersonic aircraft wing

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Buckling behavior of rene 41 tubular panels for a hypersonic aircraft wing

Content Provider	NASA Technical Reports Server (NTRS)
Author	Shideler, J. L. Ko, W. L. Fields, R. A.
Copyright Year	1986
Description	The buckling characteristics of Rene 41 tubular panels for a hypersonic aircraft wing were investigated. The panels were repeatedly tested for buckling characteristics using a hypersonic wing test structure and a universal tension/compression testing machine. The nondestructive buckling tests were carried out under different combined load conditions and in different temperature environments. The force/stiffness technique was used to determine the buckling loads of the panel. In spite of some data scattering, resulting from large extrapolations of the data fitting curve (because of the termination of applied loads at relatively low percentages of the buckling loads), the overall test data correlate fairly well with theoretically predicted buckling interaction curves. Also, the structural efficiency of the tubular panels was found to be slightly higher than that of beaded panels.
File Size	1596844
Page Count	33
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19860017181
Archival Resource Key	ark:/13960/t51g5kg7w
Language	English
Publisher Date	1986-05-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Stiffness Matrix Nondestructive Tests Thermal Protection Temperature Effects Aerodynamic Heating Rene 41 Wing Loading Buckling Hypersonic Aircraft Wing Panels Sweptback Wings Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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