Aerodynamic characteristics of two rectangular-plan-form, all moveable controls in combination with a slender body of revolution at Mach numbers from 3.00 to 6.25 Page: 3 of 40
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2 s NACA IM A55J07
employ the entire stabilizing surface for control - that is, as an all-
movable control. For various reasons, these controls are generally small
and, therefore, operate entirely within the disturbed flow field created
by the missile body. It follows, then, that wing-body interference will
usually play an important role in the aerodynamic characteristics of the
At low supersonic speeds, the nature of wing-body interference is
reasonably well understood. There is a large amount. of experimental data
available and several theories for treating the interference flows. For
the case of an all-movable wing, the theoretical methods include that of
Tucker (ref. 1) who treated only the lift, using linear theory with
approximate boundary conditions. There is also the work of Nielsen,
Kaattari, and Drake (ref. 2) which is based on a combination of linear
and slender-body theory. This method provides predictions of the lift,
pitching moment, and hinge moment. This result has been extended by
Katzen and Pitts (ref. 3) to include predictions of drag. There are, in
addition, several other methods available for low supersonic speeds. All
of these methods are, in general, based on linear theory and they have
'been found to be adequate for predicting the aerodynamic forces and moments
(with the possible exception of hinge moments) for wing-body combinations,
subject, of course, to the usual restrictions of linear theory.
At high supersonic speeds, however, the situation is not so encourag-
ing. There is not, at present, any mass of data available on the aero-
dynamic characteristics of all-movable wing-body combinations nor any
well-established theory. Since the theoretical methods used at lower
speeds are, as noted, based on linear theory, their application at high
supersonic speeds is often suspect. More comparisons with experimental
data are required before the limitations of the linearized methods can be
ascertained accurately at high Mach numbers. As a step toward providing
the needed experimental data, a program was undertaken to determine the
aerodynamic characteristics of two all-movable wing controls in combina-
tion with a slender body of revolution. These controls had rectangular
plan forms and were tested at Mach numbers from 3.00 to 6.25, angles of
attack up to 250, and angles of control deflection from -300 to +300
The results of this investigation are reported herein together with com-
parisons of the experimental characteristics with those predicted by
(b - 2rb)2
A aspect ratio (for exposed panels joined together), S
b control span
c control chord
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Wong, Thomas J. & Gloria, Hermilo R. Aerodynamic characteristics of two rectangular-plan-form, all moveable controls in combination with a slender body of revolution at Mach numbers from 3.00 to 6.25, report, December 28, 1955; (digital.library.unt.edu/ark:/67531/metadc61904/m1/3/: accessed November 17, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.