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NACA-TN-4366
The effects of an inverse-taper leading-edge flap on the aerodynamic characteristics in pitch of a wing-body combination having an aspect ratio of 3 to 45 degrees of sweepback at Mach numbers to 0.92
Year: 1958
Abstract: An investigation has been made to determine the effects of an inverse-taper leading-edge flap on the drag ad on the static-longitudinal characteristics of a swept-wing-body combination. The wing had 45° of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or twist. However, with the flap deflected, the wing had a camber and twist distribution similar to that resulting from the incorporation of conical camber in the forward portion of a plane wing. The tests were conducted over a range of Mach numbers from 0.25 to 0.92 at a Reynolds number of 3.2 million, and over a Reynolds number range of'3.2 million to 15 million at a Mach number of 0.25 with flap deflections to 16°.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:52:16Z | |
| date available | 2017-09-04T17:52:16Z | |
| date copyright | 01/01/1958 | |
| date issued | 1958 | |
| identifier other | FBOUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/175476 | |
| description abstract | An investigation has been made to determine the effects of an inverse-taper leading-edge flap on the drag ad on the static-longitudinal characteristics of a swept-wing-body combination. The wing had 45° of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or twist. However, with the flap deflected, the wing had a camber and twist distribution similar to that resulting from the incorporation of conical camber in the forward portion of a plane wing. The tests were conducted over a range of Mach numbers from 0.25 to 0.92 at a Reynolds number of 3.2 million, and over a Reynolds number range of'3.2 million to 15 million at a Mach number of 0.25 with flap deflections to 16°. | |
| language | English | |
| title | NACA-TN-4366 | num |
| title | The effects of an inverse-taper leading-edge flap on the aerodynamic characteristics in pitch of a wing-body combination having an aspect ratio of 3 to 45 degrees of sweepback at Mach numbers to 0.92 | en |
| type | standard | |
| page | 58 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1958 | |
| contenttype | fulltext |