Show simple item record

NACA-TN-1553

Compressive strength of 24S-T aluminum-alloy flat panels with longitudinal formed hat-section stiffeners having four ratios of stiffener thickness to skin thickness

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:13:42Z
date available2017-09-04T15:13:42Z
date copyright01/01/1948
date issued1948
identifier otherMBATYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/12409
description abstractResults are presented for a test program on 24S-T aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. The results for panels in which the thickness are presented and incorporated with the results previously presented for panels in which the thicknesses of the stiffener material are 0.63 and 1.00 times the skin thickness. The results, presented in tabular and graphical form, show the effect of the relative dimensions of a panel on the buckling stress and the average stress at failure.
languageEnglish
titleNACA-TN-1553num
titleCompressive strength of 24S-T aluminum-alloy flat panels with longitudinal formed hat-section stiffeners having four ratios of stiffener thickness to skin thicknessen
typestandard
page42
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1948
contenttypefulltext
subject keywordsALCOA
subject keywordsALLOY
subject keywordsALLOYS
subject keywordsALUMINUM
subject keywordsBUCKLING
subject keywordsCHARTS
subject keywordsCOMBINATIONS
subject keywordsCOMPRESSIVE
subject keywordsHAT
subject keywordsSHAPED
subject keywordsSHEET
subject keywordsSKIN
subject keywordsSTIFFENER
subject keywordsSTIFFENERS
subject keywordsSTRENGTH
subject keywordsSTRESSED


Files in this item

Thumbnail
Name:
MBATYDAAAAAAAAAA.pdf
Size:
1.026Mb
Format:
PDF
View/Open

This item appears in the following Collection(s)

Show simple item record