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NACA-TN-1110
Two-dimensional wind-tunnel investigation of an approximately 14-percent-thick NACA 66-series-type airfoil section with a double slotted flap
Year: 1946
Abstract: INTRODUCTION
Tests were made in the Langley two-dimensional low-turbulence tunnels of an airfoil section equipped with a double slotted flap designed for application to a fighter type airplane. Preliminary design of the airplane indicated that a maximum section lift coefficient of approximately 3.00 was necessary if the airplane were to have the specified landing and take-off characteristics. The purpose of this investigation was to develop suitable double-slotted-flap configuration for use on this airplane.
The tests were made of a 24-inch-chord model of an intermediate airfoil section formed by a straight-line fairing between a modified NACA 66(215)-214 root section and a modified NACA 65(112)-213 tip section. The investigation included the determination of the aerodynamic characteristics of the plain airfoil section and of a considerable number of double-slotted-flap arrangements. Five different vanes were employed in conjunction with the double-slotted-flap tests. The position and deflection of the vanes relative to the airfoil were varied in an effort to obtain a high value of the maximum section lift coefficient. The results of this investigation indicate that a maximum section lift coefficient of 3.00 can be obtained with the use of a suitable double-slotted-flap arrangement.
Tests were made in the Langley two-dimensional low-turbulence tunnels of an airfoil section equipped with a double slotted flap designed for application to a fighter type airplane. Preliminary design of the airplane indicated that a maximum section lift coefficient of approximately 3.00 was necessary if the airplane were to have the specified landing and take-off characteristics. The purpose of this investigation was to develop suitable double-slotted-flap configuration for use on this airplane.
The tests were made of a 24-inch-chord model of an intermediate airfoil section formed by a straight-line fairing between a modified NACA 66(215)-214 root section and a modified NACA 65(112)-213 tip section. The investigation included the determination of the aerodynamic characteristics of the plain airfoil section and of a considerable number of double-slotted-flap arrangements. Five different vanes were employed in conjunction with the double-slotted-flap tests. The position and deflection of the vanes relative to the airfoil were varied in an effort to obtain a high value of the maximum section lift coefficient. The results of this investigation indicate that a maximum section lift coefficient of 3.00 can be obtained with the use of a suitable double-slotted-flap arrangement.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:47:01Z | |
| date available | 2017-09-04T18:47:01Z | |
| date copyright | 01/01/1946 | |
| date issued | 1946 | |
| identifier other | KKYIYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsessionid=3826AF679D40527318548F1EFDEC014A/handle/yse/228219 | |
| description abstract | INTRODUCTION Tests were made in the Langley two-dimensional low-turbulence tunnels of an airfoil section equipped with a double slotted flap designed for application to a fighter type airplane. Preliminary design of the airplane indicated that a maximum section lift coefficient of approximately 3.00 was necessary if the airplane were to have the specified landing and take-off characteristics. The purpose of this investigation was to develop suitable double-slotted-flap configuration for use on this airplane. The tests were made of a 24-inch-chord model of an intermediate airfoil section formed by a straight-line fairing between a modified NACA 66(215)-214 root section and a modified NACA 65(112)-213 tip section. The investigation included the determination of the aerodynamic characteristics of the plain airfoil section and of a considerable number of double-slotted-flap arrangements. Five different vanes were employed in conjunction with the double-slotted-flap tests. The position and deflection of the vanes relative to the airfoil were varied in an effort to obtain a high value of the maximum section lift coefficient. The results of this investigation indicate that a maximum section lift coefficient of 3.00 can be obtained with the use of a suitable double-slotted-flap arrangement. | |
| language | English | |
| title | NACA-TN-1110 | num |
| title | Two-dimensional wind-tunnel investigation of an approximately 14-percent-thick NACA 66-series-type airfoil section with a double slotted flap | en |
| type | standard | |
| page | 37 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1946 | |
| contenttype | fulltext |