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High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0.6

Description: Report presenting an investigation of the damping-in-roll characteristics of a 35 degree sweptback wing, with and without vertical fins, through a range of Mach numbers in the high speed 7- by 10-foot tunnel utilizing a free-to-roll technique. The damping-in-roll coefficient increased in magnitude with Mach number in the manner indicated by theory and generally was found to increase in magnitude with angle of attack over the range tested.
Date: May 10, 1949
Creator: Myers, Boyd C., II & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department
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Effects of Mach number and sweep on the damping-in-roll characteristics of wings of aspect ratio 4

Description: An investigation of the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, three sweep angles at the quarter chord line, and the NACA 65A006 section as determined through a range of Mach numbers and angles of attack.
Date: June 27, 1949
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Partner: UNT Libraries Government Documents Department
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Damping-in-Roll Characteristics of a 42.7 Degree Sweptback Wing as Determined From a Wind-Tunnel Investigation of a Twisted Semispan Wing

Description: Report presenting an investigation to determine the damping-in-roll characteristics of a 42.7 degree sweptback wing using a linearly twisted wing to represent a rolling wing. Results regarding the effect of the airfoil contour, damping-in-roll coefficient, wing-tip helix angle, and theoretical results are provided.
Date: August 8, 1949
Creator: Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department
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Effects of sweep on the damping-in-roll characteristics of three sweptback wings having an aspect ratio of 4 at transonic speeds

Description: Report presenting the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, an NACA 65A006 airfoil section, and three different sweep angles at a range of Mach numbers and angles of attack. The data were obtained in the 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique. Results regarding the damping-in-roll parameter, angle of attack, and lift-curve slope are provided.
Date: December 14, 1950
Creator: Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department
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