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NACA-TN-3314
A technique utilizing rocket-propelled test vehicles for the measurement of the damping in roll of sting-mounted models and some initial results for delta and unswept tapered wings
Year: 1955
Abstract: A free-flight test technique with which the damping in roll of sting-mounted wings and wing-fuselage combinations can be obtained over the high subsonic, transonic, and supersonic speed range with rocket-propelled test vehicles is described, and some results for delta and unswept tapered wings are presented. Results for all the configurations tested show that damping in roll was maintained throughout the Mach number range investigated (0.6 to 1.7) and that subsonic damping-in-roll results agreed with theoretical values within experimental accuracy. In the lower supersonic region these results differ from the values predicted by linearized-flow theory; however, the agreement improved with increasing Mach number. Increased section thickness decreased the damping in roll of the delta wings throughout the Mach number range investigated.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:49:36Z | |
| date available | 2017-09-04T17:49:36Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | EUNUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/172870 | |
| description abstract | A free-flight test technique with which the damping in roll of sting-mounted wings and wing-fuselage combinations can be obtained over the high subsonic, transonic, and supersonic speed range with rocket-propelled test vehicles is described, and some results for delta and unswept tapered wings are presented. Results for all the configurations tested show that damping in roll was maintained throughout the Mach number range investigated (0.6 to 1.7) and that subsonic damping-in-roll results agreed with theoretical values within experimental accuracy. In the lower supersonic region these results differ from the values predicted by linearized-flow theory; however, the agreement improved with increasing Mach number. Increased section thickness decreased the damping in roll of the delta wings throughout the Mach number range investigated. | |
| language | English | |
| title | NACA-TN-3314 | num |
| title | A technique utilizing rocket-propelled test vehicles for the measurement of the damping in roll of sting-mounted models and some initial results for delta and unswept tapered wings | en |
| type | standard | |
| page | 26 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |