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NACA-RM-L54C29
Wind-tunnel investigation at high subsonic speeds of the stability characteristics of a complete model having sweptback-,M-,W-,and cranked-wing plan forms and several horizontal-tail locations
Year: 1954
Abstract: INTRODUCTION
The use of thin swept wings to improve the high-speed-performance characteristics of airplanes has resulted in abrupt reductions in longitudinal stability that have been described as "pitch-up". Results of an intensive study of means for alleviating the pitch-up tendency on configurations having a 45° sweptback wing of aspect ratio 4.0 and taper ratio 0.3 have been reported in references 1 to 4. Of the various wing modifications and tail positions previously studied, it appeared that satisfactory high-lift stability (particularly at mach numbers near 0.9) could be obtained only by combining one of the most effective leading-edge modifications with a tail position well below the wing-chord plane. The present investigation was undertaken to determine conditions under which satisfactory stability might be obtained when the basic swept-wing plan form is modified by ore extreme measures than those considered in references 1 to 4. The modifications to the basic swept wing were made by shearing the airfoil sections to form composite wing plan forms described as the M-, W-, and cranked types. Longitudinal characteristics were determined for a model equipped with each of these wings (including the basic sweptback wing) and with the horizontal-tail located at various heights. Some lateral stability characteristics were determined for two of these wings.
The use of thin swept wings to improve the high-speed-performance characteristics of airplanes has resulted in abrupt reductions in longitudinal stability that have been described as "pitch-up". Results of an intensive study of means for alleviating the pitch-up tendency on configurations having a 45° sweptback wing of aspect ratio 4.0 and taper ratio 0.3 have been reported in references 1 to 4. Of the various wing modifications and tail positions previously studied, it appeared that satisfactory high-lift stability (particularly at mach numbers near 0.9) could be obtained only by combining one of the most effective leading-edge modifications with a tail position well below the wing-chord plane. The present investigation was undertaken to determine conditions under which satisfactory stability might be obtained when the basic swept-wing plan form is modified by ore extreme measures than those considered in references 1 to 4. The modifications to the basic swept wing were made by shearing the airfoil sections to form composite wing plan forms described as the M-, W-, and cranked types. Longitudinal characteristics were determined for a model equipped with each of these wings (including the basic sweptback wing) and with the horizontal-tail located at various heights. Some lateral stability characteristics were determined for two of these wings.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:38:26Z | |
| date available | 2017-09-04T18:38:26Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | JPSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://lib.yabesh.ir/std/handle/yse/220209 | |
| description abstract | INTRODUCTION The use of thin swept wings to improve the high-speed-performance characteristics of airplanes has resulted in abrupt reductions in longitudinal stability that have been described as "pitch-up". Results of an intensive study of means for alleviating the pitch-up tendency on configurations having a 45° sweptback wing of aspect ratio 4.0 and taper ratio 0.3 have been reported in references 1 to 4. Of the various wing modifications and tail positions previously studied, it appeared that satisfactory high-lift stability (particularly at mach numbers near 0.9) could be obtained only by combining one of the most effective leading-edge modifications with a tail position well below the wing-chord plane. The present investigation was undertaken to determine conditions under which satisfactory stability might be obtained when the basic swept-wing plan form is modified by ore extreme measures than those considered in references 1 to 4. The modifications to the basic swept wing were made by shearing the airfoil sections to form composite wing plan forms described as the M-, W-, and cranked types. Longitudinal characteristics were determined for a model equipped with each of these wings (including the basic sweptback wing) and with the horizontal-tail located at various heights. Some lateral stability characteristics were determined for two of these wings. | |
| language | English | |
| title | NACA-RM-L54C29 | num |
| title | Wind-tunnel investigation at high subsonic speeds of the stability characteristics of a complete model having sweptback-,M-,W-,and cranked-wing plan forms and several horizontal-tail locations | en |
| type | standard | |
| page | 73 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |