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NACA-RM-L9J04
Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61
Year: 1949
Abstract: INTRODUCTION
The behavior of auxiliary fuel tanks mounted at the tips of straight wings is well established (reference 1) in the region of speeds where compressibility and aeroelastic effects are of secondary importance- As the speeds of aircraft increase, however, compressibility and aeroelasticity become of major importance even on a wing without a tip tank 80 that the necessity for obtaining information on the effect of tip mounted tanks at high speeds is apparent.
The results presented in this paper were obtained in the Langley high-speed 7- by 10-foot tunnel and include data obtained on two identical wing plan form having different airfoil sections, with and without a tip tank, over a Mach number range from 0.60 to 0.90. Also shown are the effects of two modifications t o the trailing portion of me of the airfoil sections. Modifications t o the basic profile were accomplished by extending the wing trailing edge. The lift; and pitching-moment coefficients of the tank alone in the presence of the rigid-unswept-wing model are included in the results presented. Pitching moments of the tank alone are presented about the 40-percent-tip-chord point which is considered representative of the elastic-axis location of a flexible wing. The effect of horizontal tank stabilizing fine on the properties of the tank alone in presence ,of the wing are shown.
The behavior of auxiliary fuel tanks mounted at the tips of straight wings is well established (reference 1) in the region of speeds where compressibility and aeroelastic effects are of secondary importance- As the speeds of aircraft increase, however, compressibility and aeroelasticity become of major importance even on a wing without a tip tank 80 that the necessity for obtaining information on the effect of tip mounted tanks at high speeds is apparent.
The results presented in this paper were obtained in the Langley high-speed 7- by 10-foot tunnel and include data obtained on two identical wing plan form having different airfoil sections, with and without a tip tank, over a Mach number range from 0.60 to 0.90. Also shown are the effects of two modifications t o the trailing portion of me of the airfoil sections. Modifications t o the basic profile were accomplished by extending the wing trailing edge. The lift; and pitching-moment coefficients of the tank alone in the presence of the rigid-unswept-wing model are included in the results presented. Pitching moments of the tank alone are presented about the 40-percent-tip-chord point which is considered representative of the elastic-axis location of a flexible wing. The effect of horizontal tank stabilizing fine on the properties of the tank alone in presence ,of the wing are shown.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:05:31Z | |
| date available | 2017-09-04T18:05:31Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | GJSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/188415 | |
| description abstract | INTRODUCTION The behavior of auxiliary fuel tanks mounted at the tips of straight wings is well established (reference 1) in the region of speeds where compressibility and aeroelastic effects are of secondary importance- As the speeds of aircraft increase, however, compressibility and aeroelasticity become of major importance even on a wing without a tip tank 80 that the necessity for obtaining information on the effect of tip mounted tanks at high speeds is apparent. The results presented in this paper were obtained in the Langley high-speed 7- by 10-foot tunnel and include data obtained on two identical wing plan form having different airfoil sections, with and without a tip tank, over a Mach number range from 0.60 to 0.90. Also shown are the effects of two modifications t o the trailing portion of me of the airfoil sections. Modifications t o the basic profile were accomplished by extending the wing trailing edge. The lift; and pitching-moment coefficients of the tank alone in the presence of the rigid-unswept-wing model are included in the results presented. Pitching moments of the tank alone are presented about the 40-percent-tip-chord point which is considered representative of the elastic-axis location of a flexible wing. The effect of horizontal tank stabilizing fine on the properties of the tank alone in presence ,of the wing are shown. | |
| language | English | |
| title | NACA-RM-L9J04 | num |
| title | Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61 | en |
| type | standard | |
| page | 32 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |