Damping in roll of straight and 45 degree swept wings of various taper ratios determined at high subsonic, transonic, and supersonic speeds with rocket-powered models

Claude E. Sanders, Jr.
naca-rm-l51h14
Oct 1951


Rocket-powered flight tests have been conducted to determine the damping in roll of several wings of 0 and 45 degrees quarter-chord-line sweep with various taper ratios. The Mach number range of these tests was from 0.8 to 1.45.

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http://naca.central.cranfield.ac.uk/reports/1951/naca-rm-l51h14.pdf