Low-speed wind-tunnel investigation of a fixed and a free-floating wing-tip aileron on a wing with leading edge swept back 51.3 degrees

R. G. MacLeod
naca-rm-l51h16a
Feb 1952

A low-speed wind-tunnel investigation was made on a semispan wing swept back 51.3 degrees at the leading edge with an aspect ratio of 4.47 and and NACA 65(1)-012 airfoil section normal to the 0.556 chord line to determine the effectiveness of a half-delta tip aileron throughout a large angle-of-attack range.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1952/naca-rm-l51h16a.pdf