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NACA-RM-A8F15
Investigation of a thin wing of aspect ratio 4 in the Ames 12-foot pressure wind tunnel. II - the effect of constant-chord leading-and trailing-edge flaps on the low-speed characteristics of the wing
Year: 1948
Abstract: INTRODUCTION
For supersonic aircraft, the wings of which are not swept behind the Mach cone, airfoil sections -with sharp leading edges are considered necessary to minimize the drag due to wave resistance. The maximum lift of such a wing profile at subsonic speeds is relatively low due to the occurrence of laminar separation at the wing leading edge at small angles of attack. Accordingly auxiliary lift-producing devices are essential to provide the aircraft with acceptable landing and take-off characteristics.
In order to ascertain the effectiveness of constant-chord leading and trailing-edge flaps applied to such a wing, tests of a semispan model have been conducted in the Ames Moot pressure wind tunnel. The model represented a wing of aspect ratio 4, a taper ratio of 0.50, with a sharp-edge diamond profile of thickness ratio 0.045. The tests were made at Mach numbers of 0.20 and 0.30 and at a range of Reynolds numbers from 3,000,000 to 10,000,000.
For supersonic aircraft, the wings of which are not swept behind the Mach cone, airfoil sections -with sharp leading edges are considered necessary to minimize the drag due to wave resistance. The maximum lift of such a wing profile at subsonic speeds is relatively low due to the occurrence of laminar separation at the wing leading edge at small angles of attack. Accordingly auxiliary lift-producing devices are essential to provide the aircraft with acceptable landing and take-off characteristics.
In order to ascertain the effectiveness of constant-chord leading and trailing-edge flaps applied to such a wing, tests of a semispan model have been conducted in the Ames Moot pressure wind tunnel. The model represented a wing of aspect ratio 4, a taper ratio of 0.50, with a sharp-edge diamond profile of thickness ratio 0.045. The tests were made at Mach numbers of 0.20 and 0.30 and at a range of Reynolds numbers from 3,000,000 to 10,000,000.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:22:06Z | |
| date available | 2017-09-04T16:22:06Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | TPCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/85458 | |
| description abstract | INTRODUCTION For supersonic aircraft, the wings of which are not swept behind the Mach cone, airfoil sections -with sharp leading edges are considered necessary to minimize the drag due to wave resistance. The maximum lift of such a wing profile at subsonic speeds is relatively low due to the occurrence of laminar separation at the wing leading edge at small angles of attack. Accordingly auxiliary lift-producing devices are essential to provide the aircraft with acceptable landing and take-off characteristics. In order to ascertain the effectiveness of constant-chord leading and trailing-edge flaps applied to such a wing, tests of a semispan model have been conducted in the Ames Moot pressure wind tunnel. The model represented a wing of aspect ratio 4, a taper ratio of 0.50, with a sharp-edge diamond profile of thickness ratio 0.045. The tests were made at Mach numbers of 0.20 and 0.30 and at a range of Reynolds numbers from 3,000,000 to 10,000,000. | |
| language | English | |
| title | NACA-RM-A8F15 | num |
| title | Investigation of a thin wing of aspect ratio 4 in the Ames 12-foot pressure wind tunnel. II - the effect of constant-chord leading-and trailing-edge flaps on the low-speed characteristics of the wing | en |
| type | standard | |
| page | 44 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |