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NACA-RM-L8G05
Full-scale investigation of an equilateral triangular wing having 10-percent-thick biconvex airfoil sections
Year: 1948
Abstract: INTRODUCTION
A wing having triangular plan form, 60° of sweepback at the leading edge, and 10-percent-tuck biconvex airfoil sections has been tested in the Langley full-scale tunnel as part of a general investigation of the low-speed characteristics of probable hi&-speed-airplane configurations.
The investigation included tests to determine the effects of semispan and f full-span leading edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the triangular wing. Tests were made of several leading-edge and trailing-edge flap combinations to determine the optimum low-speed flap configuration. The lateral Characteristics of the unflapped triangular. wing, with and without a Vertical fin installed, were also determined.
A wing having triangular plan form, 60° of sweepback at the leading edge, and 10-percent-tuck biconvex airfoil sections has been tested in the Langley full-scale tunnel as part of a general investigation of the low-speed characteristics of probable hi&-speed-airplane configurations.
The investigation included tests to determine the effects of semispan and f full-span leading edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the triangular wing. Tests were made of several leading-edge and trailing-edge flap combinations to determine the optimum low-speed flap configuration. The lateral Characteristics of the unflapped triangular. wing, with and without a Vertical fin installed, were also determined.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:04:59Z | |
| date available | 2017-09-04T16:04:59Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | RUSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/68228 | |
| description abstract | INTRODUCTION A wing having triangular plan form, 60° of sweepback at the leading edge, and 10-percent-tuck biconvex airfoil sections has been tested in the Langley full-scale tunnel as part of a general investigation of the low-speed characteristics of probable hi&-speed-airplane configurations. The investigation included tests to determine the effects of semispan and f full-span leading edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the triangular wing. Tests were made of several leading-edge and trailing-edge flap combinations to determine the optimum low-speed flap configuration. The lateral Characteristics of the unflapped triangular. wing, with and without a Vertical fin installed, were also determined. | |
| language | English | |
| title | NACA-RM-L8G05 | num |
| title | Full-scale investigation of an equilateral triangular wing having 10-percent-thick biconvex airfoil sections | en |
| type | standard | |
| page | 36 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |