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NACA-TN-2468
Investigation at low speed of 45 degrees and 60 degrees sweptback, tapered, low-drag wings equipped with various types of full-span, trailing-edge flaps
Year: 1951
Abstract: An investigation was made in the Georgia Institute of Technology 9-foot wind tunnel to determine the low-speed aerodynamic characteristics of two sweptback, low-drag, tapered wings equipped with full-span split and slotted flaps and special types of trailing-edge flaps. Two sweep angles of 45° and 60°, measured at the quarter chord, were used.
Although emphasis was placed on attempts to obtain higher maximum lift coefficients, the results show no appreciable gain in clmax for either the split flap or the spcial flaps on the 60° wing. These same flaps did produce an increment in clmax on 45° model, however. The slotted flap produced by far the largest increase in lift on both models.
The effect of the flaps on drag and pitching moment is the same as that indicated by other test data available. The slotted flap caused the largest increase in pitching moment for a given deflection angle. All flap configurations increased the stability of both wings.
Although emphasis was placed on attempts to obtain higher maximum lift coefficients, the results show no appreciable gain in clmax for either the split flap or the spcial flaps on the 60° wing. These same flaps did produce an increment in clmax on 45° model, however. The slotted flap produced by far the largest increase in lift on both models.
The effect of the flaps on drag and pitching moment is the same as that indicated by other test data available. The slotted flap caused the largest increase in pitching moment for a given deflection angle. All flap configurations increased the stability of both wings.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:44:15Z | |
| date available | 2017-09-04T17:44:15Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | EFPTYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/167280 | |
| description abstract | An investigation was made in the Georgia Institute of Technology 9-foot wind tunnel to determine the low-speed aerodynamic characteristics of two sweptback, low-drag, tapered wings equipped with full-span split and slotted flaps and special types of trailing-edge flaps. Two sweep angles of 45° and 60°, measured at the quarter chord, were used. Although emphasis was placed on attempts to obtain higher maximum lift coefficients, the results show no appreciable gain in clmax for either the split flap or the spcial flaps on the 60° wing. These same flaps did produce an increment in clmax on 45° model, however. The slotted flap produced by far the largest increase in lift on both models. The effect of the flaps on drag and pitching moment is the same as that indicated by other test data available. The slotted flap caused the largest increase in pitching moment for a given deflection angle. All flap configurations increased the stability of both wings. | |
| language | English | |
| title | NACA-TN-2468 | num |
| title | Investigation at low speed of 45 degrees and 60 degrees sweptback, tapered, low-drag wings equipped with various types of full-span, trailing-edge flaps | en |
| type | standard | |
| page | 54 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |