درباره ما
NACA-TN-3693
Preliminary investigation of the effectiveness of a sliding flap in deflecting a propeller slipstream downward for vertical take-off
Year: 1956
Abstract: An investigation of the effectiveness of a wing equipped with a sliding flap and a leading-edge slat in deflecting a propeller slipstream downward for vertical take-off has been conducted in a static-thrust facility at the Langley Aeronautical Laboratory. The sliding flap, which, in comparison with flap configurations previously tested, makes possible a more forward location of the point at which flow turning begins, was expected to minimize diving moments and, at the same time, to keep a reasonable amount of the wing "fixed" for structural purposes. The results of the investigation indicate that, for a -comparable downward deflection of the slipstream, the diving moments associated with the sliding-flap configuration are appreciably smaller than those of the slotted-f lap configuration previously investigated. The addition of a leading-edge slat increased the turning angles achieved, particularly in the ground-effect region, and reduced the diving moment further. Extension of the chord of the flaps increased the turning angle achieved but increased the diving moments and caused some loss in turning efficiency.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:50:45Z | |
| date available | 2017-09-04T17:50:45Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | EXNUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/173988 | |
| description abstract | An investigation of the effectiveness of a wing equipped with a sliding flap and a leading-edge slat in deflecting a propeller slipstream downward for vertical take-off has been conducted in a static-thrust facility at the Langley Aeronautical Laboratory. The sliding flap, which, in comparison with flap configurations previously tested, makes possible a more forward location of the point at which flow turning begins, was expected to minimize diving moments and, at the same time, to keep a reasonable amount of the wing "fixed" for structural purposes. The results of the investigation indicate that, for a -comparable downward deflection of the slipstream, the diving moments associated with the sliding-flap configuration are appreciably smaller than those of the slotted-f lap configuration previously investigated. The addition of a leading-edge slat increased the turning angles achieved, particularly in the ground-effect region, and reduced the diving moment further. Extension of the chord of the flaps increased the turning angle achieved but increased the diving moments and caused some loss in turning efficiency. | |
| language | English | |
| title | NACA-TN-3693 | num |
| title | Preliminary investigation of the effectiveness of a sliding flap in deflecting a propeller slipstream downward for vertical take-off | en |
| type | standard | |
| page | 26 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |