Experimental flutter investigation of a thin unswept wing at transonic speeds Page: 4 of 26
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NACA RM L55Ai8 35
b wing semichord, in. or ft (as required by dimensional
considerations)
c wing chord, 2b,. in.
fhl first bending natural frequency, cps
fh2 second bending natural frequency, cps
fa uncoupled first torsion frequency about elastic axis, cps
g structural damping coefficient
gh structural damping coefficient for bending mode
gM structural damping coefficient for torsion mode
I wing mass moment of inertia about elastic axis per unit
length, b-sec2
Ixx wing section area moment of inertia, in.4
length of exposed wing measured perpendicular to wing
root, in.
M Mach number
m mass of wing per unit length, lb-sec2/sq in.
q dynamic pressure at flutter, ~pVe, lb/sq ft
r, nondimensional radius of gyration of wing about elastic
axis, Jmb2, fraction of semichord
t wing thickness, in.
V stream velocity at flutter, ft/sec
x nondimensional wing section center-of-gravity location
C measured from elastic axis, positive rearward of elas-
tic axis, percent of semichord
U-I
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Pratt, George L. Experimental flutter investigation of a thin unswept wing at transonic speeds, report, April 4, 1955; (https://digital.library.unt.edu/ark:/67531/metadc61296/m1/4/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.