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NACA-RM-L7G09
Investigation of high-lift and stall-control devices on a NACA 64-series 42 degrees sweptback wing with and without fuselage
Year: 1947
Abstract: INTRODUCTION
Wind-tunnel tests in the Langley 19-foot pressure tunnel (reference 1) showed that a 42 sweptback wing of aspect ration 4 and NACA 641-112 airfoil sections was longitudinally unstable at the stall and also had relatively low values of maximum lift coefficient even with semispan split flaps. Preliminary tests of several devices which could be expected to increase the maximum lift coefficient or improve the stability characteristics at the stall showed promising results (reference 2); hence, the effects of these devices and additional devices have been studied in greater detail. The results of both investigations are summarized in the present report.
Devices investigated were leading-edge flaps and slats, trailing-edge split and extended split flaps, upper-surface split flaps, and upper surface fences. The devices were investigated individually and in various combinations on the wing with and without a fuselage. The effects of the leading-edge flaps on the lateral stability characteristics of the wing with and without the fuselage were also investigated.
The main part of the investigation was conducted at a Reynolds number of 6,840,000 but the effects of varying the Reynolds number through a range from 3,000,000 to 6,840,000 were determined for some of the combinations.
Wind-tunnel tests in the Langley 19-foot pressure tunnel (reference 1) showed that a 42 sweptback wing of aspect ration 4 and NACA 641-112 airfoil sections was longitudinally unstable at the stall and also had relatively low values of maximum lift coefficient even with semispan split flaps. Preliminary tests of several devices which could be expected to increase the maximum lift coefficient or improve the stability characteristics at the stall showed promising results (reference 2); hence, the effects of these devices and additional devices have been studied in greater detail. The results of both investigations are summarized in the present report.
Devices investigated were leading-edge flaps and slats, trailing-edge split and extended split flaps, upper-surface split flaps, and upper surface fences. The devices were investigated individually and in various combinations on the wing with and without a fuselage. The effects of the leading-edge flaps on the lateral stability characteristics of the wing with and without the fuselage were also investigated.
The main part of the investigation was conducted at a Reynolds number of 6,840,000 but the effects of varying the Reynolds number through a range from 3,000,000 to 6,840,000 were determined for some of the combinations.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:01:56Z | |
| date available | 2017-09-04T16:01:56Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | RMMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/65189 | |
| description abstract | INTRODUCTION Wind-tunnel tests in the Langley 19-foot pressure tunnel (reference 1) showed that a 42 sweptback wing of aspect ration 4 and NACA 641-112 airfoil sections was longitudinally unstable at the stall and also had relatively low values of maximum lift coefficient even with semispan split flaps. Preliminary tests of several devices which could be expected to increase the maximum lift coefficient or improve the stability characteristics at the stall showed promising results (reference 2); hence, the effects of these devices and additional devices have been studied in greater detail. The results of both investigations are summarized in the present report. Devices investigated were leading-edge flaps and slats, trailing-edge split and extended split flaps, upper-surface split flaps, and upper surface fences. The devices were investigated individually and in various combinations on the wing with and without a fuselage. The effects of the leading-edge flaps on the lateral stability characteristics of the wing with and without the fuselage were also investigated. The main part of the investigation was conducted at a Reynolds number of 6,840,000 but the effects of varying the Reynolds number through a range from 3,000,000 to 6,840,000 were determined for some of the combinations. | |
| language | English | |
| title | NACA-RM-L7G09 | num |
| title | Investigation of high-lift and stall-control devices on a NACA 64-series 42 degrees sweptback wing with and without fuselage | en |
| type | standard | |
| page | 48 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext |