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NACA-RM-53L22
Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy
Year: 1954
Abstract: Additional static and fatigue tests were made on aluminum-alloy 355-T6 sand-cast specimens. Direct-stress fatigue tests were made on plate-type specimens with a single l-inch-diameter as-cast cored hole and on specimens in which the cored hole was reamed to 11/16-inch diameter. In addition, direct-stress fatigue tests were made on 0.300-inch-diameter specimens, with various degrees of porosity, machined from the butt ends of plate-type specimens. Comparisons are made with the results of earlier tests, on plate-type specimens with variations in design details such as bosses and ribs, given in NACA Technical Note 2394.
Within the range of stresses used, there were no significant differences in the fatigue strengths of sand-cast specimens with a l-inch-diameter cored hole when tested with the hole in the as-cast condition or with the hole enlarged l/16 of an inch in diameter by reaming. When the results of tests on the specimens with a l-inch-diameter cored hole are compared with results, from the previous investigation, for specimens in which a small cast boss was removed and a l-inch-diameter hole drilled and reamed in the center of the plate-type specimen there is found to be no significant difference in the results except for a slight difference in the static strengths.
Within the range of stresses used, there were no significant differences in the fatigue strengths of sand-cast specimens with a l-inch-diameter cored hole when tested with the hole in the as-cast condition or with the hole enlarged l/16 of an inch in diameter by reaming. When the results of tests on the specimens with a l-inch-diameter cored hole are compared with results, from the previous investigation, for specimens in which a small cast boss was removed and a l-inch-diameter hole drilled and reamed in the center of the plate-type specimen there is found to be no significant difference in the results except for a slight difference in the static strengths.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:29:12Z | |
| date available | 2017-09-04T17:29:12Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | CRONEEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/152257 | |
| description abstract | Additional static and fatigue tests were made on aluminum-alloy 355-T6 sand-cast specimens. Direct-stress fatigue tests were made on plate-type specimens with a single l-inch-diameter as-cast cored hole and on specimens in which the cored hole was reamed to 11/16-inch diameter. In addition, direct-stress fatigue tests were made on 0.300-inch-diameter specimens, with various degrees of porosity, machined from the butt ends of plate-type specimens. Comparisons are made with the results of earlier tests, on plate-type specimens with variations in design details such as bosses and ribs, given in NACA Technical Note 2394. Within the range of stresses used, there were no significant differences in the fatigue strengths of sand-cast specimens with a l-inch-diameter cored hole when tested with the hole in the as-cast condition or with the hole enlarged l/16 of an inch in diameter by reaming. When the results of tests on the specimens with a l-inch-diameter cored hole are compared with results, from the previous investigation, for specimens in which a small cast boss was removed and a l-inch-diameter hole drilled and reamed in the center of the plate-type specimen there is found to be no significant difference in the results except for a slight difference in the static strengths. | |
| language | English | |
| title | NACA-RM-53L22 | num |
| title | Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy | en |
| type | standard | |
| page | 25 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |