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NACA-RM-A9C21
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed
Year: 1949
Abstract: INTRODUCTION
A coordinated program is being conducted at Ames Aeronautical Laboratory t o provide information throughout an extensive range of Mach and Reynolds numbers on a wing-fuselage combination employing a wing with the leading edge swept back 63° and having an aspect ratio of 3.5. According to the theoretical considerations of reference 1, a wing of this plan form should be capable of efficient flight at supersonic Mach numbers up t o 1.5. Experimental results from tests of wings of this p k form at high Mach or Reynolds numbers are presented in references 2, 3, and 4.
A wing-fuselage combination having a wing of the plan form just described was investigated in one of the Ames 7- by 10-foot wind tunnels to evaluate the effectiveness of various flaps and particularly their capacity for eliminating the large changes in the longitudinal stability which have been found to occur above a lift coefficient of 0.4 (reference 4). In this connection, a drooped-nose flap and an extended-nose flap were tested in conjunction with trailing-edge flaps. Furthermore, an investigation was made to determine the optimum chordwise position of split flaps and the effectiveness of elevons of two different plan forms.
A coordinated program is being conducted at Ames Aeronautical Laboratory t o provide information throughout an extensive range of Mach and Reynolds numbers on a wing-fuselage combination employing a wing with the leading edge swept back 63° and having an aspect ratio of 3.5. According to the theoretical considerations of reference 1, a wing of this plan form should be capable of efficient flight at supersonic Mach numbers up t o 1.5. Experimental results from tests of wings of this p k form at high Mach or Reynolds numbers are presented in references 2, 3, and 4.
A wing-fuselage combination having a wing of the plan form just described was investigated in one of the Ames 7- by 10-foot wind tunnels to evaluate the effectiveness of various flaps and particularly their capacity for eliminating the large changes in the longitudinal stability which have been found to occur above a lift coefficient of 0.4 (reference 4). In this connection, a drooped-nose flap and an extended-nose flap were tested in conjunction with trailing-edge flaps. Furthermore, an investigation was made to determine the optimum chordwise position of split flaps and the effectiveness of elevons of two different plan forms.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:35:36Z | |
| date available | 2017-09-04T15:35:36Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | OQCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/37539 | |
| description abstract | INTRODUCTION A coordinated program is being conducted at Ames Aeronautical Laboratory t o provide information throughout an extensive range of Mach and Reynolds numbers on a wing-fuselage combination employing a wing with the leading edge swept back 63° and having an aspect ratio of 3.5. According to the theoretical considerations of reference 1, a wing of this plan form should be capable of efficient flight at supersonic Mach numbers up t o 1.5. Experimental results from tests of wings of this p k form at high Mach or Reynolds numbers are presented in references 2, 3, and 4. A wing-fuselage combination having a wing of the plan form just described was investigated in one of the Ames 7- by 10-foot wind tunnels to evaluate the effectiveness of various flaps and particularly their capacity for eliminating the large changes in the longitudinal stability which have been found to occur above a lift coefficient of 0.4 (reference 4). In this connection, a drooped-nose flap and an extended-nose flap were tested in conjunction with trailing-edge flaps. Furthermore, an investigation was made to determine the optimum chordwise position of split flaps and the effectiveness of elevons of two different plan forms. | |
| language | English | |
| title | NACA-RM-A9C21 | num |
| title | Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed | en |
| type | standard | |
| page | 48 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |