درباره ما
NACA-TN-2151
Estimation of the damping in roll of supersonic-leading-edge wing-body combinations
Year: 1950
Abstract: A description is given of a linear-theory method for the estimation of the damping in roll of supersonic-leading-edge wings mounted on cylindrical bodies. The error resulting from an approximation essential to the method is shown to be small.
The damping in roll is calculated for configurations having rectangular and triangular wings; for most of the range of variables the net effect of the body is to decrease the damping in roll.. The body effect is small for body diameters less than about 30 percent of the wing span but increases rapidly with body size above this value.
The damping in roll is calculated for configurations having rectangular and triangular wings; for most of the range of variables the net effect of the body is to decrease the damping in roll.. The body effect is small for body diameters less than about 30 percent of the wing span but increases rapidly with body size above this value.
Subject: BODIES
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:39:05Z | |
| date available | 2017-09-04T16:39:05Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | VKBUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/102696 | |
| description abstract | A description is given of a linear-theory method for the estimation of the damping in roll of supersonic-leading-edge wings mounted on cylindrical bodies. The error resulting from an approximation essential to the method is shown to be small. The damping in roll is calculated for configurations having rectangular and triangular wings; for most of the range of variables the net effect of the body is to decrease the damping in roll.. The body effect is small for body diameters less than about 30 percent of the wing span but increases rapidly with body size above this value. | |
| language | English | |
| title | NACA-TN-2151 | num |
| title | Estimation of the damping in roll of supersonic-leading-edge wing-body combinations | en |
| type | standard | |
| page | 22 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext | |
| subject keywords | BODIES | |
| subject keywords | COMBINATIONS | |
| subject keywords | DAMPING | |
| subject keywords | DELTA | |
| subject keywords | FLOW | |
| subject keywords | FUSELAGE | |
| subject keywords | INTERFERENCE | |
| subject keywords | LINEAR | |
| subject keywords | RECTANGULAR | |
| subject keywords | ROLL | |
| subject keywords | SUPERSONIC | |
| subject keywords | THEORIES | |
| subject keywords | WING | |
| subject keywords | WINGS |