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NASA-CR-2443
Development of a Fowler flap system for a high performance general aviation airfoil
Year: 1974
Abstract: A two-dimensional wind-tunnel evaluation of two Fowler flap configurations on the new GA(W)-1 airfoil was conducted. One configuration used a computer-designed 29-percent chord Fowler flap. The second configuration was modified to have increased Fowler action with a 30-percent chord flap. Force, pressure, and flow-visualization data were obtained at Reynolds numbers of 2.2 million to 2.9 million. Optimum slot geometry and performance were found to be close to computer predictions. A C sub L max of 3.8 was achieved. Optimum flap deflection, slot gap, and flap overlap are presented as functions of C sub L. Tests were made with the lower surface cusp filled in to show the performance penalties that result. Some data on the effects of adding vortex generators and hinged-plate spoilers were obtained.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:20:08Z | |
| date available | 2017-09-04T15:20:08Z | |
| date copyright | 01/01/1974 | |
| date issued | 1974 | |
| identifier other | MVMKAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/20030 | |
| description abstract | A two-dimensional wind-tunnel evaluation of two Fowler flap configurations on the new GA(W)-1 airfoil was conducted. One configuration used a computer-designed 29-percent chord Fowler flap. The second configuration was modified to have increased Fowler action with a 30-percent chord flap. Force, pressure, and flow-visualization data were obtained at Reynolds numbers of 2.2 million to 2.9 million. Optimum slot geometry and performance were found to be close to computer predictions. A C sub L max of 3.8 was achieved. Optimum flap deflection, slot gap, and flap overlap are presented as functions of C sub L. Tests were made with the lower surface cusp filled in to show the performance penalties that result. Some data on the effects of adding vortex generators and hinged-plate spoilers were obtained. | |
| language | English | |
| title | NASA-CR-2443 | num |
| title | Development of a Fowler flap system for a high performance general aviation airfoil | en |
| type | standard | |
| page | 118 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1974 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIDED | |
| subject keywords | AIRCRAFT | |
| subject keywords | AIRFOIL | |
| subject keywords | AVIATION | |
| subject keywords | COEFFICIENTS | |
| subject keywords | COMPUTER | |
| subject keywords | DESIGN | |
| subject keywords | DISTRIBUTION | |
| subject keywords | EDGE | |
| subject keywords | FLAPS | |
| subject keywords | FLOW | |
| subject keywords | GAW | |
| subject keywords | GENERAL | |
| subject keywords | PRESSURE | |
| subject keywords | SPEED | |
| subject keywords | SUBSONIC | |
| subject keywords | TESTS | |
| subject keywords | TRAILING | |
| subject keywords | TUNNEL | |
| subject keywords | VISUALIZATION | |
| subject keywords | WIND |