Experimental Determination Of Damping In Pitch Of Swept And Delta Wings At Supersonic Mach Numbers
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Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers
| Author | : John A. Moore |
| Publisher | : |
| Total Pages | : 28 |
| Release | : 1957 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
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The damping-in-pitch derivative was determined experimentally at Mach numbers of 2.96 and 3.92 for two delta wings having aspect ratios of 2 and 3 and for one sweptback tapered wing having an aspect ratio of 3 by using a free-oscillation technique. The tests were made at Reynolds numbers based on mean aerodynamic chord from 4,000,000 to 12,000,000 for an angle-of-attack range of zero to 10 degrees. The reduced-frequency parameter ranged from 0.006 to 0.022.
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