Investigation of flap-type ailerons on an untapered wing having an aspect ratio of 3.7, 45 degree sweepback, and an NACA 65A009 airfoil section: Transonic-bump method Page: 4 of 20

                                
NACA RM LOG03

C a          rolling-moment coefficient produced by the control
(rolling-moment coefficient of the entire wing with
control deflected minus rolling-moment coefficient
of the entire wing with undeflected control)
q            effective dynamic pressure over span of model, pounds
per square foot ( pv2)
S            twice wing area of semispan model, 0.116 square foot
b            twice span of semispan model, 0.654 foot
c            mean aerodynamic chord of wing, 0.177 foot
c            local wing chord, feet
y            spanwise distance from plane of symmetry, feet
Yi           spanwise distance from plane of symmetry to inboard end
of control, feet
p            mass density of air, slugs per cubic foot
V            free-stream air velocity, feet per second
M            effective Mach number over span of model
Ma           average chordwise local Mach number
MN           local Mach number
R            Reynolds number of wing based on c
a            angle of attack, degrees referred to wing root
chord line
6            control deflection relative to wing-chord plane
measured perpendicular to control hinge axis, degrees
ba           control span measured perpendicular to plane of symmetry,
feet
(83CL

a+ .