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NACA-TN-4174
Wind-tunnel investigation of the static lateral stability characteristics of wind-fuselage combinations at high subsonic speeds taper-ratio series
Year: 1957
Abstract: An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of variations In taper ratio within the range of 0.3 to 1.0 on the static lateral stability characteristics at high subsonic speeds of wing-fuselage combinations having wings of 45° sweepback at the quarter-chord line and an aspect ratio of 4. As has been shown in previous experimental investigations of other wing plan forms, the parameter cζβ/cL, which expresses the rate of change of effective dihedral with lift coefficient, was found to increase at the high subsonic Mach numbers as the force-break Mach number was approached. Above the force-break Mach number Cζβ/CL decreased in magnitude with the severity of the break increasing with a decrease in taper ratio. The experimental variation of cζβ/CL increases negatively with taper ratio and agrees well with the predicted trend; however, the experimental values are shown to be appreciably larger than the predicted values. At low and moderate lift coefficients the derivative of yawing moment due to sideslip cnb and lateral force due to sideslip Cyβ for the wing-fuselage combinations are contributed almost entirely by the fuselage alone; however, at high lift coefficients the effects of the wing are quite large.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:16:39Z | |
| date available | 2017-09-04T16:16:39Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | TAOUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/80022 | |
| description abstract | An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of variations In taper ratio within the range of 0.3 to 1.0 on the static lateral stability characteristics at high subsonic speeds of wing-fuselage combinations having wings of 45° sweepback at the quarter-chord line and an aspect ratio of 4. As has been shown in previous experimental investigations of other wing plan forms, the parameter cζβ/cL, which expresses the rate of change of effective dihedral with lift coefficient, was found to increase at the high subsonic Mach numbers as the force-break Mach number was approached. Above the force-break Mach number Cζβ/CL decreased in magnitude with the severity of the break increasing with a decrease in taper ratio. The experimental variation of cζβ/CL increases negatively with taper ratio and agrees well with the predicted trend; however, the experimental values are shown to be appreciably larger than the predicted values. At low and moderate lift coefficients the derivative of yawing moment due to sideslip cnb and lateral force due to sideslip Cyβ for the wing-fuselage combinations are contributed almost entirely by the fuselage alone; however, at high lift coefficients the effects of the wing are quite large. | |
| language | English | |
| title | NACA-TN-4174 | num |
| title | Wind-tunnel investigation of the static lateral stability characteristics of wind-fuselage combinations at high subsonic speeds taper-ratio series | en |
| type | standard | |
| page | 26 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |