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NACA-RM-L51J08
Effect of vertical location of a horizontal tail on the static longitudinal stability characteristics of a 45 degrees sweptback-wing-fuselage combination of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)
Year: 1952
Abstract: INTRODUCTION
The design information necessary to evaluate optimum configurations for high-subsonic-speed long-range airplanes has been extended to include a 45° sweptback wing of aspect ratio 8 (references 1 and 2). This wing is in a previously unexplored aspect-ratio range for highly sweptback wings.
Previous investigations of sweptback-wing configurations (references 3 and 4) have shown that the effectiveness of a horizontal tail is influenced greatly by the vertical position of the horizontal tail relative to the wing wake. It was also indicated that the increase in the effectiveness of a horizontal tail at high lift coefficients, when it is located in the proper position, can be advantageously used to counteract the inherent instability of highly sweptback-wing-fuselage configurations of moderate and large aspect ratios.
The present investigation was made, therefore, to determine the low speed static longitudinal stability characteristics of the 450 swepback wing of aspect ratio 8 in combination with a fuselage and a horizontal tail. The tests were made at a Reynolds number of 4.0 X106 and a mach number of 0.19 for four tail positions and various flap and stall-control configurations.
The design information necessary to evaluate optimum configurations for high-subsonic-speed long-range airplanes has been extended to include a 45° sweptback wing of aspect ratio 8 (references 1 and 2). This wing is in a previously unexplored aspect-ratio range for highly sweptback wings.
Previous investigations of sweptback-wing configurations (references 3 and 4) have shown that the effectiveness of a horizontal tail is influenced greatly by the vertical position of the horizontal tail relative to the wing wake. It was also indicated that the increase in the effectiveness of a horizontal tail at high lift coefficients, when it is located in the proper position, can be advantageously used to counteract the inherent instability of highly sweptback-wing-fuselage configurations of moderate and large aspect ratios.
The present investigation was made, therefore, to determine the low speed static longitudinal stability characteristics of the 450 swepback wing of aspect ratio 8 in combination with a fuselage and a horizontal tail. The tests were made at a Reynolds number of 4.0 X106 and a mach number of 0.19 for four tail positions and various flap and stall-control configurations.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:59:43Z | |
| date available | 2017-09-04T17:59:43Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | FUSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/182758 | |
| description abstract | INTRODUCTION The design information necessary to evaluate optimum configurations for high-subsonic-speed long-range airplanes has been extended to include a 45° sweptback wing of aspect ratio 8 (references 1 and 2). This wing is in a previously unexplored aspect-ratio range for highly sweptback wings. Previous investigations of sweptback-wing configurations (references 3 and 4) have shown that the effectiveness of a horizontal tail is influenced greatly by the vertical position of the horizontal tail relative to the wing wake. It was also indicated that the increase in the effectiveness of a horizontal tail at high lift coefficients, when it is located in the proper position, can be advantageously used to counteract the inherent instability of highly sweptback-wing-fuselage configurations of moderate and large aspect ratios. The present investigation was made, therefore, to determine the low speed static longitudinal stability characteristics of the 450 swepback wing of aspect ratio 8 in combination with a fuselage and a horizontal tail. The tests were made at a Reynolds number of 4.0 X106 and a mach number of 0.19 for four tail positions and various flap and stall-control configurations. | |
| language | English | |
| title | NACA-RM-L51J08 | num |
| title | Effect of vertical location of a horizontal tail on the static longitudinal stability characteristics of a 45 degrees sweptback-wing-fuselage combination of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6) | en |
| type | standard | |
| page | 44 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |