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NACA-TN-3848
A study of several factors affecting the stability contributed by a horizontal tail at various vertical positions on a sweptback-wing airplane model
Year: 1956
Abstract: A study was made in the Langley 19-foot pressure tunnel to determine the effects of fuselage afterbody shape , split flaps, and variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail to an airplane with the wing leading edge swept back 42º. Supplementary tests were made to determine some of the characteristics of the air flow In the vicinity of the tail, the wing being equipped with 0.575-span leading-edge flaps and 0.5-span split flaps. All data were obtained at a Reynolds number 6.8 X 106.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:04:00Z | |
| date available | 2017-09-04T17:04:00Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | XYNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/127593 | |
| description abstract | A study was made in the Langley 19-foot pressure tunnel to determine the effects of fuselage afterbody shape , split flaps, and variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail to an airplane with the wing leading edge swept back 42º. Supplementary tests were made to determine some of the characteristics of the air flow In the vicinity of the tail, the wing being equipped with 0.575-span leading-edge flaps and 0.5-span split flaps. All data were obtained at a Reynolds number 6.8 X 106. | |
| language | English | |
| title | NACA-TN-3848 | num |
| title | A study of several factors affecting the stability contributed by a horizontal tail at various vertical positions on a sweptback-wing airplane model | en |
| type | standard | |
| page | 29 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |