Control Hinge-Moment and Effectiveness Characteristics of a 60 Degree Half-Delta Tip Control on a 60 Degree Delta Wing at Mach Numbers of 1.41 and 1.96 Page: 3 of 41
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2 CONFIDENTIAL 4 NACA RM L52 13
The objectionable nonlinearities in the hinge-moment variations
with both angle of attack and deflection at small angles were success-
fully eliminated by a fence located at the wing-control parting line.
The fence increased the minimum drag of the wing but caused no drag
increase at moderate and high lift coefficients at Mach numbers of 1.41
The half-delta wing-tip control has been shown to be an effective
lateral-control device at transonic and supersonic speeds and, for the
proper hinge-line location, to have relatively low hinge moments over
a given Mach number range (refs. 1 to 4). Previous investigations were
limited to low-angle conditions; it is therefore desirable to learn the
behavior of this type of control at high angles of attack and control
deflection, particularly since it is known that for delta wings the
load distribution near the tip undergoes substantial changes as the
angle of attack is increased from moderate to high values (ref. 5). In
order to furnish such information, an investigation was conducted in
the Langley 9- by 12-inch supersonic blowdown tunnel on a half-delta
control located at the tip of a 600 delta wing, similar to those of
references 2, 3, 4, and 6, at Mach numbers of 1.41 and 1.96 and Reynolds
numbers of 2.4 x 10 and 2.0 x 10 , respectively.
The aerodynamic characteristics of the complete model, as well as
control hinge moments and bending moments, were obtained throughout a
maximum control-deflection range of 300 and at angles of attack as
high as 240. A fence, mounted at the wing-control parting line, was
tested in an attempt to modify hinge-moment characteristics. Control
moments and rolling effectiveness have been compared with calculated
values. In order to give some indication of the effects of a fence on
subsonic wing characteristics, lift, drag, and pitching-moment measure-
ments obtained at a Mach number of 0.73 and a Reynolds number of
2.2 X 106 are also presented. A mathematical analysis of the optical
system, used to measure control-surface hinge moments and bending
moments, is included in the appendix.
CL lift coefficient,
CD drag coefficient, D
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Guy, Lawrence D. Control Hinge-Moment and Effectiveness Characteristics of a 60 Degree Half-Delta Tip Control on a 60 Degree Delta Wing at Mach Numbers of 1.41 and 1.96, report, October 14, 1952; (https://digital.library.unt.edu/ark:/67531/metadc59409/m1/3/: accessed April 21, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.