درباره ما
NACA-RM-A8E03
Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. II - the effectiveness and hinge moments of a constant-chord plain flap
Year: 1948
Abstract: INTRODUCTION
In various investigations of the characteristics of wings designed to operate at moderate supersonic speeds, it has been shown that the low-aspect-ratio triangular wing offers several advantages. The low aspect ratio and high taper result in structural problems less serious than those usually associated with thin wings designed for these speeds. The beneficial effects of sweep at supersonic speeds, low-pressure drag, and low drag due to lift have been shown to be theoretically possible for the triangular wing with the apex forward and leading edge swept well behind the Mach wave (reference 1). Compared with high-aspect-ratio wings having the same amount of sweep, the triangular wing gives evidence of superior longitudinal-stability characteristics at high lift coefficients.
This report presents results of tests in the Ames 12-foot pressure wind tunnel of a triangular wing equipped with a plain constant-chord trailing-edge flap. Tests of the same model with an undeflected flap were described in reference 2.
In various investigations of the characteristics of wings designed to operate at moderate supersonic speeds, it has been shown that the low-aspect-ratio triangular wing offers several advantages. The low aspect ratio and high taper result in structural problems less serious than those usually associated with thin wings designed for these speeds. The beneficial effects of sweep at supersonic speeds, low-pressure drag, and low drag due to lift have been shown to be theoretically possible for the triangular wing with the apex forward and leading edge swept well behind the Mach wave (reference 1). Compared with high-aspect-ratio wings having the same amount of sweep, the triangular wing gives evidence of superior longitudinal-stability characteristics at high lift coefficients.
This report presents results of tests in the Ames 12-foot pressure wind tunnel of a triangular wing equipped with a plain constant-chord trailing-edge flap. Tests of the same model with an undeflected flap were described in reference 2.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:26:40Z | |
| date available | 2017-09-04T15:26:40Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | NPCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/27500 | |
| description abstract | INTRODUCTION In various investigations of the characteristics of wings designed to operate at moderate supersonic speeds, it has been shown that the low-aspect-ratio triangular wing offers several advantages. The low aspect ratio and high taper result in structural problems less serious than those usually associated with thin wings designed for these speeds. The beneficial effects of sweep at supersonic speeds, low-pressure drag, and low drag due to lift have been shown to be theoretically possible for the triangular wing with the apex forward and leading edge swept well behind the Mach wave (reference 1). Compared with high-aspect-ratio wings having the same amount of sweep, the triangular wing gives evidence of superior longitudinal-stability characteristics at high lift coefficients. This report presents results of tests in the Ames 12-foot pressure wind tunnel of a triangular wing equipped with a plain constant-chord trailing-edge flap. Tests of the same model with an undeflected flap were described in reference 2. | |
| language | English | |
| title | NACA-RM-A8E03 | num |
| title | Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. II - the effectiveness and hinge moments of a constant-chord plain flap | en |
| type | standard | |
| page | 85 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |