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NACA-RM-A8D02
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees - investigation of a large-scale model at low speed
Year: 1949
Abstract: INTRODUCTION
The theory developed in reference 1 indicates that aircraft employing wings of high sweepback and high aspect ratio should be capable of efficient flighty (L/D =10) at moderate supersonic Mach numbers. To provide information necessary for the design of such an airplane, a possible configuration for a transport-type airplane suitable for flight at speeds up to 1.5 Mach number is undergoing study in the research facilities of the Ames Aeronautical Laboratory.
The design incorporates a wing with the leading edge swept back 63°, an aspect ratio of 3.5, and a taper ratio of 0.25, with a fuselage of fineness ratio 12.5
The aerodynamic characteristics of this configuration are being examined over a large range of Mach numbers and Reynolds numbers. This report presents the aerodynamic characteristics at Low speed and high Reynolds number as determined in the Ames 40-by 80-foot wind tunnel.
The theory developed in reference 1 indicates that aircraft employing wings of high sweepback and high aspect ratio should be capable of efficient flighty (L/D =10) at moderate supersonic Mach numbers. To provide information necessary for the design of such an airplane, a possible configuration for a transport-type airplane suitable for flight at speeds up to 1.5 Mach number is undergoing study in the research facilities of the Ames Aeronautical Laboratory.
The design incorporates a wing with the leading edge swept back 63°, an aspect ratio of 3.5, and a taper ratio of 0.25, with a fuselage of fineness ratio 12.5
The aerodynamic characteristics of this configuration are being examined over a large range of Mach numbers and Reynolds numbers. This report presents the aerodynamic characteristics at Low speed and high Reynolds number as determined in the Ames 40-by 80-foot wind tunnel.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:48:30Z | |
| date available | 2017-09-04T18:48:30Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | KPCTUDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsessionid=47037D83FCDCAC426159DD6E273C9FCD/handle/yse/229793 | |
| description abstract | INTRODUCTION The theory developed in reference 1 indicates that aircraft employing wings of high sweepback and high aspect ratio should be capable of efficient flighty (L/D =10) at moderate supersonic Mach numbers. To provide information necessary for the design of such an airplane, a possible configuration for a transport-type airplane suitable for flight at speeds up to 1.5 Mach number is undergoing study in the research facilities of the Ames Aeronautical Laboratory. The design incorporates a wing with the leading edge swept back 63°, an aspect ratio of 3.5, and a taper ratio of 0.25, with a fuselage of fineness ratio 12.5 The aerodynamic characteristics of this configuration are being examined over a large range of Mach numbers and Reynolds numbers. This report presents the aerodynamic characteristics at Low speed and high Reynolds number as determined in the Ames 40-by 80-foot wind tunnel. | |
| language | English | |
| title | NACA-RM-A8D02 | num |
| title | Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees - investigation of a large-scale model at low speed | en |
| type | standard | |
| page | 22 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |