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NACA-RM-L51D20
Low-speed investigation of several types of split flap on a 47.7 degrees sweptback-wing - fuselage combination of aspect ratio 5.1 at a Reynolds number of 6.0 x 10(exp 6)
Year: 1951
Abstract: INTRODUCTION
As part of an investigation to supply additional information concerning the effectiveness of various types of flaps on wings having sweptback plan forms, together with the effects of flap deflection, span and chord wise position, the effectiveness of various types of flap has been evaluated on a 47.7° sweptback-wing-fuselage combination. Reference 1 presents the results obtained from tests of single slotted flaps. The present paper reports the results of tests of flaps of the split type.
The tests were conducted in the Langley 19-foot pressure tunnel at a Reynolds number of 6.0 X106 and a Mach number of 0.14. The wing had an aspect ratio of 5.1, a taper ratio of 0.383, and NACA 64-210 airfoil sections normal to the 0.286-chord line. For most of the tests a fuselage was attached to the wing. The flaps investigated were split, extended split (Zap), rotated split, step split, and triangular, and were tested in combination with several spans of leading-edge flap.
As part of an investigation to supply additional information concerning the effectiveness of various types of flaps on wings having sweptback plan forms, together with the effects of flap deflection, span and chord wise position, the effectiveness of various types of flap has been evaluated on a 47.7° sweptback-wing-fuselage combination. Reference 1 presents the results obtained from tests of single slotted flaps. The present paper reports the results of tests of flaps of the split type.
The tests were conducted in the Langley 19-foot pressure tunnel at a Reynolds number of 6.0 X106 and a Mach number of 0.14. The wing had an aspect ratio of 5.1, a taper ratio of 0.383, and NACA 64-210 airfoil sections normal to the 0.286-chord line. For most of the tests a fuselage was attached to the wing. The flaps investigated were split, extended split (Zap), rotated split, step split, and triangular, and were tested in combination with several spans of leading-edge flap.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:26:59Z | |
| date available | 2017-09-04T17:26:59Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | CLSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/150101 | |
| description abstract | INTRODUCTION As part of an investigation to supply additional information concerning the effectiveness of various types of flaps on wings having sweptback plan forms, together with the effects of flap deflection, span and chord wise position, the effectiveness of various types of flap has been evaluated on a 47.7° sweptback-wing-fuselage combination. Reference 1 presents the results obtained from tests of single slotted flaps. The present paper reports the results of tests of flaps of the split type. The tests were conducted in the Langley 19-foot pressure tunnel at a Reynolds number of 6.0 X106 and a Mach number of 0.14. The wing had an aspect ratio of 5.1, a taper ratio of 0.383, and NACA 64-210 airfoil sections normal to the 0.286-chord line. For most of the tests a fuselage was attached to the wing. The flaps investigated were split, extended split (Zap), rotated split, step split, and triangular, and were tested in combination with several spans of leading-edge flap. | |
| language | English | |
| title | NACA-RM-L51D20 | num |
| title | Low-speed investigation of several types of split flap on a 47.7 degrees sweptback-wing - fuselage combination of aspect ratio 5.1 at a Reynolds number of 6.0 x 10(exp 6) | en |
| type | standard | |
| page | 43 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |