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NACA-RM-L9K11
Measurements of aerodynamic characteristics of a 35 degrees sweptback NACA 65-009 airfoil model with 1/4-chord bevelled-trailing-edge flap and trim tab by the NACA wing-flow method
Year: 1950
Abstract: INTRODUCTION
A wing-flaw investigation is being made to determine the characteristics of conventional low-speed aerodynamic balances at transonic speeds. In this investigation a typical sweptback airfoil-flap combination representing either a wing or a tail surface is being fitted with ¼ chord full-span flaps differing only in type of aerodynamic balance. The primary objectives of the investigation are the determination of flap hinge moments and flap effectiveness; however, it has been found convenient and desirable also to measure the lift and pitching-moment characteristics of the complete models. The first series of tests was made with a plain flap which represents the case of zero aerodynamic balance (reference 1). The second series of tests was made with a horn-balanced flap that was designed to have a large degree of- aerodynamic balance at low speeds (reference 2). The present. series of' tests was made with a bevelled-trailing-edge flap that had a trailing-edge angle of 23° in planes perpendicular to the hinge line. The true-contour NACA 65-009 section flap tested in reference 1 had a trailing-edge angle of approximately 6°.
The tests consisted of measurements of the lift , pitching moments, and hinge moments acting on a semispan airfoil-flap model having a sweepback angle of 35°, an aspect ratio of 3.07, a taper-ratio of 1.0, an NACA 65-009 section in planes perpendicular to the leading edge over the forward 75 percent of the chord, a full-span ¼ -chord beveled trailing- edge flap, and a 1/3-span by a 1/3-flap-chord trim tab. Tests were made with the flap gap both sealed and unsealed. In general, data were obtained over an angle-of-attack range of -5° to 18°, a flap-deflection range of +20°,a tab-deflection range of 0 to l0°, a Mach number range of 0.55 to 1.15, and a Reynolds number range of-about- 5OO,OOO to 1,400,000. Because the tests were run within two widely separated altitude ranges, the date can be used t o study some effects of Reynolds - number even though the highest Reynolds number encountered was small in comparison w l t h probable full-scale Reynolds numbers.
A wing-flaw investigation is being made to determine the characteristics of conventional low-speed aerodynamic balances at transonic speeds. In this investigation a typical sweptback airfoil-flap combination representing either a wing or a tail surface is being fitted with ¼ chord full-span flaps differing only in type of aerodynamic balance. The primary objectives of the investigation are the determination of flap hinge moments and flap effectiveness; however, it has been found convenient and desirable also to measure the lift and pitching-moment characteristics of the complete models. The first series of tests was made with a plain flap which represents the case of zero aerodynamic balance (reference 1). The second series of tests was made with a horn-balanced flap that was designed to have a large degree of- aerodynamic balance at low speeds (reference 2). The present. series of' tests was made with a bevelled-trailing-edge flap that had a trailing-edge angle of 23° in planes perpendicular to the hinge line. The true-contour NACA 65-009 section flap tested in reference 1 had a trailing-edge angle of approximately 6°.
The tests consisted of measurements of the lift , pitching moments, and hinge moments acting on a semispan airfoil-flap model having a sweepback angle of 35°, an aspect ratio of 3.07, a taper-ratio of 1.0, an NACA 65-009 section in planes perpendicular to the leading edge over the forward 75 percent of the chord, a full-span ¼ -chord beveled trailing- edge flap, and a 1/3-span by a 1/3-flap-chord trim tab. Tests were made with the flap gap both sealed and unsealed. In general, data were obtained over an angle-of-attack range of -5° to 18°, a flap-deflection range of +20°,a tab-deflection range of 0 to l0°, a Mach number range of 0.55 to 1.15, and a Reynolds number range of-about- 5OO,OOO to 1,400,000. Because the tests were run within two widely separated altitude ranges, the date can be used t o study some effects of Reynolds - number even though the highest Reynolds number encountered was small in comparison w l t h probable full-scale Reynolds numbers.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:35:53Z | |
| date available | 2017-09-04T18:35:53Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | JJSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=authoCA5893FD081D49A96159DD6EFDEC014A/handle/yse/217841 | |
| description abstract | INTRODUCTION A wing-flaw investigation is being made to determine the characteristics of conventional low-speed aerodynamic balances at transonic speeds. In this investigation a typical sweptback airfoil-flap combination representing either a wing or a tail surface is being fitted with ¼ chord full-span flaps differing only in type of aerodynamic balance. The primary objectives of the investigation are the determination of flap hinge moments and flap effectiveness; however, it has been found convenient and desirable also to measure the lift and pitching-moment characteristics of the complete models. The first series of tests was made with a plain flap which represents the case of zero aerodynamic balance (reference 1). The second series of tests was made with a horn-balanced flap that was designed to have a large degree of- aerodynamic balance at low speeds (reference 2). The present. series of' tests was made with a bevelled-trailing-edge flap that had a trailing-edge angle of 23° in planes perpendicular to the hinge line. The true-contour NACA 65-009 section flap tested in reference 1 had a trailing-edge angle of approximately 6°. The tests consisted of measurements of the lift , pitching moments, and hinge moments acting on a semispan airfoil-flap model having a sweepback angle of 35°, an aspect ratio of 3.07, a taper-ratio of 1.0, an NACA 65-009 section in planes perpendicular to the leading edge over the forward 75 percent of the chord, a full-span ¼ -chord beveled trailing- edge flap, and a 1/3-span by a 1/3-flap-chord trim tab. Tests were made with the flap gap both sealed and unsealed. In general, data were obtained over an angle-of-attack range of -5° to 18°, a flap-deflection range of +20°,a tab-deflection range of 0 to l0°, a Mach number range of 0.55 to 1.15, and a Reynolds number range of-about- 5OO,OOO to 1,400,000. Because the tests were run within two widely separated altitude ranges, the date can be used t o study some effects of Reynolds - number even though the highest Reynolds number encountered was small in comparison w l t h probable full-scale Reynolds numbers. | |
| language | English | |
| title | NACA-RM-L9K11 | num |
| title | Measurements of aerodynamic characteristics of a 35 degrees sweptback NACA 65-009 airfoil model with 1/4-chord bevelled-trailing-edge flap and trim tab by the NACA wing-flow method | en |
| type | standard | |
| page | 70 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext |