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NASA-CR-2696
Reflection-plane tests of spoilers on an advanced technology wing with a large Fowler flap
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:12:28Z | |
| date available | 2017-09-04T17:12:28Z | |
| date copyright | 01/01/1976 | |
| date issued | 1976 | |
| identifier other | YVMKAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/135980 | |
| description abstract | Wind tunnel experiments were conducted to determine the effectiveness of spoilers applied to a finite-span wing which utilizes the GA(W)-1 airfoil section and a 30 chord full-span Fowler flap. A series of spoiler cross sectioned shapes were tested utilizing a reflection-plane model. Five-component force characteristics and hinge moment measurements were obtained. Results confirm earlier two-dimensional tests which showed that spoilers could provide large lift increments at any flap setting, and that spoiler control reversal tendencies could be eliminated by providing a vent path from lower surface to upper surface. Performance penalties due to spoiler leakage airflow were measured. | |
| language | English | |
| title | NASA-CR-2696 | num |
| title | Reflection-plane tests of spoilers on an advanced technology wing with a large Fowler flap | en |
| type | standard | |
| page | 91 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1976 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIR | |
| subject keywords | AIRFOIL | |
| subject keywords | CONTROL | |
| subject keywords | FLAPS | |
| subject keywords | FLOW | |
| subject keywords | FORCES | |
| subject keywords | GAW | |
| subject keywords | REFLECTION | |
| subject keywords | SPOILERS | |
| subject keywords | SURFACES | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | WIND |
