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NACA-RM-L56G02
Effect of a fuselage on the low-speed longitudinal aerodynamic characteristics of a 45 degrees sweptback wing with double slotted flaps
Year: 1956
Abstract: INTRODUCTION
A wind-tunnel investigation is being made by the National Advisory Committee for Aeronautics to study the characteristics of various high-lift devices on a full-scale 45° sweptback wing. Reference 1 presents the results of tests on a 1/5-scale model equipped with the double-slotted-flap designs proposed for full-scale testing. These tests were on a wing alone, however, and the effects of the presence of a fuselage on the flap-effectiveness characteristics may be large. Therefore, the present investigation was undertaken to determine the longitudinal aerodynamic characteristics of the wing used in reference 1 with a fuselage added. The results of the present investigation are compared with the results of reference 1 to show the fuselage effects.
The investigation was made in the Langley 300 MPH 7- by 10-foot tunnel. The wing investigated had an aspect ratio of 3.7, a taper ratio of 0.41, and an average thickness ratio in a streamwise direction of 0.086. The fuselage was cylindrical and had an ogival nose. The effect of fuselage proximity on the flap characteristics was studied by simulating the fuselage with a large movable plate. The 0.35-semispan, inboard, double slotted flaps consisted of a 0.213-wing-chord main flap and either a 0.300-flap-chord vane or a 0.266-flap-chord vane. An extended plain flap was simulated by blocking the slots in the double slotted flap with 0.500-flap-chord vane. In addition, some tests were made with the flap span extended inboard to the fuselage.
The general investigation was made at a Reynolds number of 1.8 x 106. Tests of the double slotted flaps were made over a Reynolds number range of 0.9 x 106 to 3.4 x 106 with the flaps deflected about 60°.
A wind-tunnel investigation is being made by the National Advisory Committee for Aeronautics to study the characteristics of various high-lift devices on a full-scale 45° sweptback wing. Reference 1 presents the results of tests on a 1/5-scale model equipped with the double-slotted-flap designs proposed for full-scale testing. These tests were on a wing alone, however, and the effects of the presence of a fuselage on the flap-effectiveness characteristics may be large. Therefore, the present investigation was undertaken to determine the longitudinal aerodynamic characteristics of the wing used in reference 1 with a fuselage added. The results of the present investigation are compared with the results of reference 1 to show the fuselage effects.
The investigation was made in the Langley 300 MPH 7- by 10-foot tunnel. The wing investigated had an aspect ratio of 3.7, a taper ratio of 0.41, and an average thickness ratio in a streamwise direction of 0.086. The fuselage was cylindrical and had an ogival nose. The effect of fuselage proximity on the flap characteristics was studied by simulating the fuselage with a large movable plate. The 0.35-semispan, inboard, double slotted flaps consisted of a 0.213-wing-chord main flap and either a 0.300-flap-chord vane or a 0.266-flap-chord vane. An extended plain flap was simulated by blocking the slots in the double slotted flap with 0.500-flap-chord vane. In addition, some tests were made with the flap span extended inboard to the fuselage.
The general investigation was made at a Reynolds number of 1.8 x 106. Tests of the double slotted flaps were made over a Reynolds number range of 0.9 x 106 to 3.4 x 106 with the flaps deflected about 60°.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:17:25Z | |
| date available | 2017-09-04T15:17:25Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | MMYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/16854 | |
| description abstract | INTRODUCTION A wind-tunnel investigation is being made by the National Advisory Committee for Aeronautics to study the characteristics of various high-lift devices on a full-scale 45° sweptback wing. Reference 1 presents the results of tests on a 1/5-scale model equipped with the double-slotted-flap designs proposed for full-scale testing. These tests were on a wing alone, however, and the effects of the presence of a fuselage on the flap-effectiveness characteristics may be large. Therefore, the present investigation was undertaken to determine the longitudinal aerodynamic characteristics of the wing used in reference 1 with a fuselage added. The results of the present investigation are compared with the results of reference 1 to show the fuselage effects. The investigation was made in the Langley 300 MPH 7- by 10-foot tunnel. The wing investigated had an aspect ratio of 3.7, a taper ratio of 0.41, and an average thickness ratio in a streamwise direction of 0.086. The fuselage was cylindrical and had an ogival nose. The effect of fuselage proximity on the flap characteristics was studied by simulating the fuselage with a large movable plate. The 0.35-semispan, inboard, double slotted flaps consisted of a 0.213-wing-chord main flap and either a 0.300-flap-chord vane or a 0.266-flap-chord vane. An extended plain flap was simulated by blocking the slots in the double slotted flap with 0.500-flap-chord vane. In addition, some tests were made with the flap span extended inboard to the fuselage. The general investigation was made at a Reynolds number of 1.8 x 106. Tests of the double slotted flaps were made over a Reynolds number range of 0.9 x 106 to 3.4 x 106 with the flaps deflected about 60°. | |
| language | English | |
| title | NACA-RM-L56G02 | num |
| title | Effect of a fuselage on the 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 |