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NACA-TN-2175
Effect of an unswept wing on the contribution of unswept-tail configuration to the low-speed static and rolling-stability derivatives of a midwing airplane model
Year: 1950
Abstract: An investigation has been conducted in the Langley stability tunnel to determine the effect of an unswept wing on the contribution of unswept-tail configurations to the low-speed static-and rolling-stability derivatives of a midwing airplane model.
The results of the investigation show that, at Angeles of attack almost to the angle of maximum lift, there are only small differences in the tail contributions to the static-lateral-stability derivatives for configurations with wing on and with wing off. For this range of angles of attack the contributions of the vertical tail can be estimated fairly accurately by the available procedures.
The results of the investigation show that, at Angeles of attack almost to the angle of maximum lift, there are only small differences in the tail contributions to the static-lateral-stability derivatives for configurations with wing on and with wing off. For this range of angles of attack the contributions of the vertical tail can be estimated fairly accurately by the available procedures.
Subject: COMBINATION
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:13:05Z | |
| date available | 2017-09-04T17:13:05Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | YXCUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/136559 | |
| description abstract | An investigation has been conducted in the Langley stability tunnel to determine the effect of an unswept wing on the contribution of unswept-tail configurations to the low-speed static-and rolling-stability derivatives of a midwing airplane model. The results of the investigation show that, at Angeles of attack almost to the angle of maximum lift, there are only small differences in the tail contributions to the static-lateral-stability derivatives for configurations with wing on and with wing off. For this range of angles of attack the contributions of the vertical tail can be estimated fairly accurately by the available procedures. | |
| language | English | |
| title | NACA-TN-2175 | num |
| title | Effect of an unswept wing on the contribution of unswept-tail configuration to the low-speed static and rolling-stability derivatives of a midwing airplane model | en |
| type | standard | |
| page | 48 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext | |
| subject keywords | COMBINATION | |
| subject keywords | COMBINATIONS | |
| subject keywords | DOWNWASH | |
| subject keywords | FUSELAGE | |
| subject keywords | HORIZONTAL | |
| subject keywords | INTERFERENCE | |
| subject keywords | INTERFERENCES | |
| subject keywords | LATERAL | |
| subject keywords | NACA | |
| subject keywords | POSITION | |
| subject keywords | SIDEWASH | |
| subject keywords | STABILITY | |
| subject keywords | STATIC | |
| subject keywords | SURFACE | |
| subject keywords | SURFACES | |
| subject keywords | TAIL | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | WIND | |
| subject keywords | WING | |
| subject keywords | WINGS |