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NACA-ACR-L4D12
Wind-tunnel investigation of control-surface characteristics XVII - beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil
Year: 1944
Abstract: Force tests in two-dimensional flow have been made in the NACA 4- by 6-foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 airfoil with flaps having chords 20, 30, and 40 percent of the airfoil chord and 20, 30, and 40 percent of the airfoil chord and 20°, 30°, and 40° beveled trailing edges. The effect of a gap at the nose of the flaps equipped with the 30 beveled trailing edge.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:16:53Z | |
| date available | 2017-09-04T15:16:53Z | |
| date copyright | 01/01/1944 | |
| date issued | 1944 | |
| identifier other | MLBZYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/16220 | |
| description abstract | Force tests in two-dimensional flow have been made in the NACA 4- by 6-foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 airfoil with flaps having chords 20, 30, and 40 percent of the airfoil chord and 20, 30, and 40 percent of the airfoil chord and 20°, 30°, and 40° beveled trailing edges. The effect of a gap at the nose of the flaps equipped with the 30 beveled trailing edge. | |
| language | English | |
| title | NACA-ACR-L4D12 | num |
| title | Wind-tunnel investigation of control-surface characteristics XVII - beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil | en |
| type | standard | |
| page | 53 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1944 | |
| contenttype | fulltext |