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NACA-TN-3843
Experimental steady-state yawing derivatives of a 60 degrees delta-wing model as affected by changes in vertical position of the wing and in ratio of fuselage diameter to wing span
Year: 1956
Abstract: An investigation was made in the Langley stability tunnel to determine the effects on the steady-state yawing derivatives of the vertical position of the wing for a 60° delta-wing model having ratios of fuselage diameter to wing span of 0.123, 0.165, and 0.246. The test Mach number was 0.13 and the Reynolds number was 1.65 X 106. The results of the investigation indicated that for angles of attack below the stall the steady-state damping in yaw decreased (the values of the yawing-moment coefficient due to yawing became less negative) when the wing was raised from a low to a middle or high position on each of the three fuselage sizes investigated. With the vertical tail on or off, the steady-state damping in yaw increased with an increase in fuselage size. The results of calculations of the oscillatory damping in yaw for the model with the large fuselage indicated that the effects of wing position would be opposite to those determined under steady-state conditions. For angles of attack below the stall, raising the wing produced a positive increment in the rolling moment due to yawing and fuselage size had little effect on this parameter.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:34:49Z | |
| date available | 2017-09-04T16:34:49Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | UYNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/98374 | |
| description abstract | An investigation was made in the Langley stability tunnel to determine the effects on the steady-state yawing derivatives of the vertical position of the wing for a 60° delta-wing model having ratios of fuselage diameter to wing span of 0.123, 0.165, and 0.246. The test Mach number was 0.13 and the Reynolds number was 1.65 X 106. The results of the investigation indicated that for angles of attack below the stall the steady-state damping in yaw decreased (the values of the yawing-moment coefficient due to yawing became less negative) when the wing was raised from a low to a middle or high position on each of the three fuselage sizes investigated. With the vertical tail on or off, the steady-state damping in yaw increased with an increase in fuselage size. The results of calculations of the oscillatory damping in yaw for the model with the large fuselage indicated that the effects of wing position would be opposite to those determined under steady-state conditions. For angles of attack below the stall, raising the wing produced a positive increment in the rolling moment due to yawing and fuselage size had little effect on this parameter. | |
| language | English | |
| title | NACA-TN-3843 | num |
| title | Experimental steady-state yawing derivatives of a 60 degrees delta-wing model as affected by changes in vertical position of the wing and in ratio of fuselage diameter to wing span | en |
| type | standard | |
| page | 21 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |