Flight investigation to determine the hinge moments of a beveled-edge aileron on a 45 degree sweptback wing at transonic and low supersonic speeds

William N. Gardner, Howard J. Curfman, Jr.
naca-rm-l7h26
Nov 1947


In an effort to determine the reason for loss of roll stabilization at supercritical speeds in flights of the NACA supersonic lateral stability and control research pilotless aircraft RM-1, a model was equipped with a balance to measure aileron hinge moments in flight. The results of the test indicate that the particular aileron design used, 20 degrees beveled edge in combination with 0.52c (sub a) overhang balance, had reasonably low hinge moments up to the critical speed range, but as the critical speed was exceeded, the hinge moments first increased quite rapidly and then decreased.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1947/naca-rm-l7h26.pdf