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NACA-RM-L50E26
Damping in roll of rectangular wings of several aspect ratios and NACA 65A-series airfoil sections of several thickness ratios at transonic and supersonic speeds as determined with rocket-powered models
Year: 1950
Abstract: INTRODUCTION
A damping-in-roll investigation has been conducted for a series of wings of several aspect ratios and airfoil thickness ratios using the NACA 65A-series airfoil section. Previous damping-in-roll tests of rectangular wings by this technique (reference 1) indicated that experimental damping would vary with airfoil thickness ratio; therefore, the present series of tests were conducted t o determine the relationship between the damping in roll for both thickness ratio and aspect ratio.
The test wings were mounted on identical fuselages incorporating canted nozzles, as described in reference 1. The damping-in-roll coefficient and the total-drag coefficient were obtained for each configuration at zero lift through a Mach number range of approximately 0.8 to 1.4, corresponding to Reynolds numbers from 3 X 106 to 8 X 106. The models were tested in flight at the Pilotless Aircraft Research Station at Wallops Island, Va.
A damping-in-roll investigation has been conducted for a series of wings of several aspect ratios and airfoil thickness ratios using the NACA 65A-series airfoil section. Previous damping-in-roll tests of rectangular wings by this technique (reference 1) indicated that experimental damping would vary with airfoil thickness ratio; therefore, the present series of tests were conducted t o determine the relationship between the damping in roll for both thickness ratio and aspect ratio.
The test wings were mounted on identical fuselages incorporating canted nozzles, as described in reference 1. The damping-in-roll coefficient and the total-drag coefficient were obtained for each configuration at zero lift through a Mach number range of approximately 0.8 to 1.4, corresponding to Reynolds numbers from 3 X 106 to 8 X 106. The models were tested in flight at the Pilotless Aircraft Research Station at Wallops Island, Va.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:42:33Z | |
| date available | 2017-09-04T15:42:33Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | PJSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/44822 | |
| description abstract | INTRODUCTION A damping-in-roll investigation has been conducted for a series of wings of several aspect ratios and airfoil thickness ratios using the NACA 65A-series airfoil section. Previous damping-in-roll tests of rectangular wings by this technique (reference 1) indicated that experimental damping would vary with airfoil thickness ratio; therefore, the present series of tests were conducted t o determine the relationship between the damping in roll for both thickness ratio and aspect ratio. The test wings were mounted on identical fuselages incorporating canted nozzles, as described in reference 1. The damping-in-roll coefficient and the total-drag coefficient were obtained for each configuration at zero lift through a Mach number range of approximately 0.8 to 1.4, corresponding to Reynolds numbers from 3 X 106 to 8 X 106. The models were tested in flight at the Pilotless Aircraft Research Station at Wallops Island, Va. | |
| language | English | |
| title | NACA-RM-L50E26 | num |
| title | Damping in roll of rectangular wings of several aspect ratios and NACA 65A-series airfoil sections of several thickness ratios at transonic and supersonic speeds as determined with rocket-powered models | en |
| type | standard | |
| page | 18 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext |