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NASA MEMO 6-5-59 REV A
Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of the Static and Dynamic Stability Derivatives of an Airplane Model with an Unswept Wing and a High Horizontal Tail
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:21:10Z | |
| date available | 2017-09-04T15:21:10Z | |
| date copyright | 01/01/1959 | |
| date issued | 1959 | |
| identifier other | MYMKAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/21167 | |
| description abstract | Results are presented of a wind-tunnel investigation to evaluate the static and dynamic stability derivatives of a model with a low-aspect-ratio unswept wing and a high horizontal tail. In addition to results for the complete model, results were also obtained of the body alone, body and wing, and body and tail. Data were obtained in the Mach number range from 0.65 to 2.2, at a Reynolds number of 2 million based on the wing mean aerodynamic chord. The angle-off attack range for most of the data was -11.5º to 180º. A limited amount of data was obtained with fixed transition. | |
| language | English | |
| title | NASA MEMO 6-5-59 REV A | num |
| title | Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of the Static and Dynamic Stability Derivatives of an Airplane Model with an Unswept Wing and a High Horizontal Tail | en |
| type | standard | |
| page | 80 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1959 | |
| contenttype | fulltext |
