Experimental determination of the damping in roll and aileron rolling effectiveness of three wings having 2 degree, 42 degree and 62 degree sweepback

Charles V. Bennett, Joseph L. Johnson
naca-tn-1278
May 1947


Tests have been made to determine the damping in roll and the aileron rolling effectiveness of three wings have 2 degree, 42 degree, and 62 degree sweepback. The wing with the 2 degree sweepback had an aspect ratio of 10 and the wings with 42 degree and 62 degree sweepback, which were obtained by rotating the panels of the wing with a 2 degree sweepback about the 0.50-root-chord point while the length of the 0.50-chord line was held constant, had aspect ratios of 5.0 and 2.5, respectively.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1947/naca-tn-1278.pdf