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NASA NACA-RM-L56A10
Low-speed longitudinal aerodynamic characteristics of a 45 degrees sweptback wing with double slotted flaps
Year: 1956
Abstract: INTRODUCTION
An investigation is being made by the National Advisory Committee for Aeronautics to study the characteristics of various high-lift devices on a full-scale 45O sweptback wing. One-fifth scale tests of the double slotted- flap designs proposed for tests at full scale were made in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of the flaps on the longitudinal aerodynamic characteristics of the sweptback wing. The wing had an aspect ratio of 3.7, symmetrical sections, a taper ratio of 0.41, and an average stream wise thickness ratio of 0.086.
In order that the design of the double slotted flaps developed in the small-scale tests can be used in the full-scale tests, the same span of flap (0.35 semispan) and the same forward limit of space for retraction (0.735 wing chord line) were used. Two double-slotted-flap configurations were used. For one, a ratio of vane chord to flap chord of existing two dimensional data (ref. 1). The flap, rearward of the vane, was 0.213 wing chord. For the other design, a smaller vane (0.266 flap chord), fixed to the flap, was chosen because it would require a less complicated retracting mechanism.
For comparison with the double-slotted-flap characteristics, the characteristics of a single-slotted-flap was simulated by blocking either of the slots, and the extended plain flap by blocking both slots.
An investigation is being made by the National Advisory Committee for Aeronautics to study the characteristics of various high-lift devices on a full-scale 45O sweptback wing. One-fifth scale tests of the double slotted- flap designs proposed for tests at full scale were made in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of the flaps on the longitudinal aerodynamic characteristics of the sweptback wing. The wing had an aspect ratio of 3.7, symmetrical sections, a taper ratio of 0.41, and an average stream wise thickness ratio of 0.086.
In order that the design of the double slotted flaps developed in the small-scale tests can be used in the full-scale tests, the same span of flap (0.35 semispan) and the same forward limit of space for retraction (0.735 wing chord line) were used. Two double-slotted-flap configurations were used. For one, a ratio of vane chord to flap chord of existing two dimensional data (ref. 1). The flap, rearward of the vane, was 0.213 wing chord. For the other design, a smaller vane (0.266 flap chord), fixed to the flap, was chosen because it would require a less complicated retracting mechanism.
For comparison with the double-slotted-flap characteristics, the characteristics of a single-slotted-flap was simulated by blocking either of the slots, and the extended plain flap by blocking both slots.
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NASA NACA-RM-L56A10
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:36:08Z | |
| date available | 2017-09-04T15:36:08Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | ORSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/38141 | |
| description abstract | INTRODUCTION An investigation is being made by the National Advisory Committee for Aeronautics to study the characteristics of various high-lift devices on a full-scale 45O sweptback wing. One-fifth scale tests of the double slotted- flap designs proposed for tests at full scale were made in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of the flaps on the longitudinal aerodynamic characteristics of the sweptback wing. The wing had an aspect ratio of 3.7, symmetrical sections, a taper ratio of 0.41, and an average stream wise thickness ratio of 0.086. In order that the design of the double slotted flaps developed in the small-scale tests can be used in the full-scale tests, the same span of flap (0.35 semispan) and the same forward limit of space for retraction (0.735 wing chord line) were used. Two double-slotted-flap configurations were used. For one, a ratio of vane chord to flap chord of existing two dimensional data (ref. 1). The flap, rearward of the vane, was 0.213 wing chord. For the other design, a smaller vane (0.266 flap chord), fixed to the flap, was chosen because it would require a less complicated retracting mechanism. For comparison with the double-slotted-flap characteristics, the characteristics of a single-slotted-flap was simulated by blocking either of the slots, and the extended plain flap by blocking both slots. | |
| language | English | |
| title | NASA NACA-RM-L56A10 | num |
| title | Low-speed longitudinal aerodynamic characteristics of a 45 degrees sweptback wing with double slotted flaps | en |
| type | standard | |
| page | 33 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |