Investigations of the damping in roll of swept and tapered wings at supersonic speeds Page: 4 of 36
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NACA RM 153Al3 Sillilil 3
ATE angle of sweep of wing trailing edge, positive for sweepback
M free-stream Mach number
4 Mach angle, sin -
p angular rolling velocity
q free-stream dynamic pressure
R Reynolds number based on mean aerodynamic chord of wing
t maximum wing thickness
V free-stream velocity
pb/2V helix angle generated by wing tip in roll
L rolling moment
C1 rolling-moment coefficient, L/qSb
Cg damping-in-roll derivative, aC, pb
All tests were conducted in the Langley 9-inch supersonic tunnel,
which is a continuous-operation closed-circuit type in which the stream
pressure, temperature, and humidity conditions can be controlled and
regulated. Different test Mach numbers are provided by interchangeable
nozzle blocks which form test sections approximately 9 inches square.
ThrOughout the present tests, the moisture content in the tunnel was
kept sufficiently low so that the effects of condensation in the super-
sonic nozzle were negligible.
Models, Support, and Rolling-Moment Balance
The pertinent wing characteristics are presented in table I. All
but .two of the wings were constructed of 3/16-inch-thick, SAE 4130 steel
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McDearmon, Russell W. & Heinke, Harry S., Jr. Investigations of the damping in roll of swept and tapered wings at supersonic speeds, report, March 3, 1953; (https://digital.library.unt.edu/ark:/67531/metadc59536/m1/4/: accessed April 25, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.