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 |
ISBN-10 | : UOM:39015086466177 |
ISBN-13 | : |
Rating | : 4/5 ( Downloads) |
Download or read book Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers written by John A. Moore and published by . This book was released on 1957 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.