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NACA-TR-571
Pressure distribution over a rectangular airfoil with a partial-span split flap
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:29:17Z | |
| date available | 2017-09-04T18:29:17Z | |
| date copyright | 01/01/1937 | |
| date issued | 1937 | |
| identifier other | ISWUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho146/handle/yse/211436 | |
| description abstract | This report presents the results of pressure-distribution tests of a Clark y wing model with a partial-span split flap made to determine the distribution of air loads over both the wing and the flap. The model was used in conjunction with a reflection plane in the NACA 7 by 10 foot wind tunnel. The 20-percent-chord split flap extended over the inboard 60 percent of the semispan. The tests were made at various flap deflections up to 45 degrees and covered a range of angles of attack from zero lift to approximately maximum lift for each deflection. | |
| language | English | |
| title | NACA-TR-571 | num |
| title | Pressure distribution over a rectangular airfoil with a partial-span split flap | en |
| type | standard | |
| page | 12 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1937 | |
| contenttype | fulltext | |
| subject keywords | DISTRIBUTION | |
| subject keywords | FLAPS | |
| subject keywords | FORCES | |
| subject keywords | LOAD | |
| subject keywords | PRESSURE | |
| subject keywords | RECTANGULAR | |
| subject keywords | SPLIT | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | WIND | |
| subject keywords | WINGS |
