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Fatigue strengths of aircraft materials axial load-fatigue tests on unnotched sheet specimens of 24S-T3 and 75S-T6 aluminum alloys and of SAE 4130 steel

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:27:38Z
date available2017-09-04T15:27:38Z
date copyright01/01/1951
date issued1951
identifier otherAVONEEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/28591
description abstractThis report presents information on the axial-load fatigue behavior of unnotched specimens of each of three sheet materials: 24S-T3 and 75S-T6 aluminum alloys and normalized SAE 4130 steel.
The experimental investigation of these materials included the following items:
1. Determination of fatigue strengths, in tests at a speed of about 1100 cycles per minute, covering a range of mean loads from zero to a high tensile value and, for each loading condition, lifetimes from 10,000 to 10,000,000 cycles
2. Determination of fatigue strengths in tests at a slower speed of about 90 cycles per minute
3. Several measurements of damage or strengthening at one stress level due to previous loading at another stress level; these tests included interchanging the order of application of high stress level and low stress level
In several respects, fatigue test data are extended beyond those previously available. However, results are in general agreement with such previously reported data as are available for comparison, The main observation unpredictable from previous work is that fatigue strengths at 90 cycles per minute appear, in some ranges of loading, appreciably lower (up to 10 percent) than corresponding strengths at 1100 cycles per minute.
languageEnglish
titleNACA-TN-2324num
titleFatigue strengths of aircraft materials axial load-fatigue tests on unnotched sheet specimens of 24S-T3 and 75S-T6 aluminum alloys and of SAE 4130 steelen
typestandard
page64
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1951
contenttypefulltext


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