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 / John D. Bird, Byron M. Jaquet, John W. Cowan.
Results 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 Lang...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1951.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2483. |
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| Summary: | Results 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 1,070,000 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 is included. |
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| Item Description: | "October 1951." NACA TN Number 2483. |
| Physical Description: | 19 pages : illustrations ; 28 cm. |
| Bibliography: | Includes bibliographical references. |