درباره ما
NACA-TN-4185
Wind-tunnel investigation of effect of sweep on rolling derivatives at angles of attack up to 13 degrees and at high subsonic Mach numbers, including a semiempirical method of estimating the rolling derivatives
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:45:47Z | |
| date available | 2017-09-04T16:45:47Z | |
| date copyright | 01/01/1958 | |
| date issued | 1958 | |
| identifier other | WAOUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/109091 | |
| description abstract | An investigation was performed in the Langley high-speed 7-by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0° to 130 and at high subsonic Mach numbers. The wings had sweep angles of 3.60°, 32.6°,45°, and 0.60° at the quarter-chord line, and aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative cζp at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative cζp was experience over the largest ranges of angle of attack and Mach for the 32.6° sweptback wing. | |
| language | English | |
| title | NACA-TN-4185 | num |
| title | Wind-tunnel investigation of effect of sweep on rolling derivatives at angles of attack up to 13 degrees and at high subsonic Mach numbers, including a semiempirical method of estimating the rolling derivatives | en |
| type | standard | |
| page | 48 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1958 | |
| contenttype | fulltext |
