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NACA-RM-L51F22
Investigation of low-speed lateral control and hinge-moment characteristics of a 20-percent-chord plain aileron on a 47.7 degrees sweptback wing of aspect ratio 5.1 at a Reynolds number of 6.0 x 10(exp 6)
Year: 1951
Abstract: INTRODUCTION
Previous investigations of plain flap-type ailerons on sweptback wings (references 1 to 3) have shown that the aileron effectiveness in the low lift range can be predicted by semiempirical means based on simple sweep theory. The effectiveness of the aileron at the higher lift coefficients, however, cannot be calculated because of the early separation of flow over the wing (reference 4). An investigation was made on a 47.7º sweptback wing of aspect ratio 5.1 employing a 20-percent-chord outboard aileron to provide information on the aileron effectiveness on a wing of relatively higher aspect ratio and sweep than has previously been investigated. The tests were made at a Reynolds number of 6.0 x 106 and a Mach number of 0.14. These tests are part of a general investigation of the subject wing and the longitudinal stability characteristics have been reported in references 4 to 6.
Previous investigations of plain flap-type ailerons on sweptback wings (references 1 to 3) have shown that the aileron effectiveness in the low lift range can be predicted by semiempirical means based on simple sweep theory. The effectiveness of the aileron at the higher lift coefficients, however, cannot be calculated because of the early separation of flow over the wing (reference 4). An investigation was made on a 47.7º sweptback wing of aspect ratio 5.1 employing a 20-percent-chord outboard aileron to provide information on the aileron effectiveness on a wing of relatively higher aspect ratio and sweep than has previously been investigated. The tests were made at a Reynolds number of 6.0 x 106 and a Mach number of 0.14. These tests are part of a general investigation of the subject wing and the longitudinal stability characteristics have been reported in references 4 to 6.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:56:10Z | |
| date available | 2017-09-04T17:56:10Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | FLSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/179304 | |
| description abstract | INTRODUCTION Previous investigations of plain flap-type ailerons on sweptback wings (references 1 to 3) have shown that the aileron effectiveness in the low lift range can be predicted by semiempirical means based on simple sweep theory. The effectiveness of the aileron at the higher lift coefficients, however, cannot be calculated because of the early separation of flow over the wing (reference 4). An investigation was made on a 47.7º sweptback wing of aspect ratio 5.1 employing a 20-percent-chord outboard aileron to provide information on the aileron effectiveness on a wing of relatively higher aspect ratio and sweep than has previously been investigated. The tests were made at a Reynolds number of 6.0 x 106 and a Mach number of 0.14. These tests are part of a general investigation of the subject wing and the longitudinal stability characteristics have been reported in references 4 to 6. | |
| language | English | |
| title | NACA-RM-L51F22 | num |
| title | Investigation of low-speed lateral control and hinge-moment characteristics of a 20-percent-chord plain aileron on a 47.7 degrees sweptback wing of aspect ratio 5.1 at a Reynolds number of 6.0 x 10(exp 6) | en |
| type | standard | |
| page | 33 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |