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NACA-TN-2483
Effect of fuselage and tail surfaces on low-speed yawing characteristics of a swept-wing model as determined in curved-flow test section of Langley stability tunnel
Year: 1951
Abstract: Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage and tail surfaces on the rotary derivatives in yawing flight of a transonic-airplane configuration having 45 degrees sweptback wing and tail surfaces. The tests were run in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1.07 X 10 to the sixth power and consisted of balance measurements throughout the angle-of-attack range for several flight-path radii of curvature. The results are compared with data from forced-oscillation and free-oscillation tests, and a description of testing techniques used is included.
Subject: AERODYNAMICS
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:00:09Z | |
| date available | 2017-09-04T16:00:09Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | RHLUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/63299 | |
| description abstract | Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage and tail surfaces on the rotary derivatives in yawing flight of a transonic-airplane configuration having 45 degrees sweptback wing and tail surfaces. The tests were run in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1.07 X 10 to the sixth power and consisted of balance measurements throughout the angle-of-attack range for several flight-path radii of curvature. The results are compared with data from forced-oscillation and free-oscillation tests, and a description of testing techniques used is included. | |
| language | English | |
| title | NACA-TN-2483 | num |
| title | Effect of fuselage and tail surfaces on low-speed yawing characteristics of a swept-wing model as determined in curved-flow test section of Langley stability tunnel | en |
| type | standard | |
| page | 20 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMICS | |
| subject keywords | AIRPLANES | |
| subject keywords | COMBINATIONS | |
| subject keywords | COMPLETE | |
| subject keywords | DAMPING | |
| subject keywords | DERIVITIVES | |
| subject keywords | FUSELAGE | |
| subject keywords | LONGITUDINAL | |
| subject keywords | RESEARCH | |
| subject keywords | STABILITY | |
| subject keywords | STATIC | |
| subject keywords | SWEEP | |
| subject keywords | TAIL | |
| subject keywords | TECHNIQUES | |
| subject keywords | TUNNELS | |
| subject keywords | WIND | |
| subject keywords | WING | |
| subject keywords | WINGS |