Low-speed static longitudinal stability characteristics of a canard model having a 60 degrees triangular wing and horizontal tail Page: 4 of 17
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NAOA RM L9E17
a--- d
and 16 percent of the area of the wing were used in the investigation.
The results obtained with the flat-late airfoil sections used on the
model are approximately the same as would have been obtained. with a
conventional section because the aerodynamic characteristics of delta
wings are virtually independent of the airfoil section at low scale.
This characteristic has been established by comparison of the aero-
dynamic characteristics of some flat--plate delta wings from reference 2
with some German data on delta wings (reference 3) having NACA 0012
airfoil sections and with some unpublished. data on" a 600 delta wing
with an NAGA 0015--64 airfoil section.
I
Force tests to determine the aerodynamic characteristics of the
model were made on the six-component balance in the Langley free-flight
tunnel. These facilities are described in references 4 and 5. All the
force tests were made at a dynamic pressure of 3.0 pounds per square
foot which corresponds to a Reynolds number of approximately 483,000
based on the wing mean aerodynamic chord.
Tests were made to determine the static longitudinal stability and
control characteristics of the model with the horizontal tail off, fixed
at various angles of incidence, and floating freely at various tab
deflections.
RESULTS AND DISCUSSION
The longitudinal stability and control characteristics of the model
may be analyzed in two ways, depending on the use that is made of the
horizontal tail. As previously mentioned, the tail may be used simply
to overcome the change of stability which results from the change in
aerodynamic-center location between subsonic and supersonic speed condi-
tions. In this case longitudinal control may. be obtained by deflecting
the ailerons up or down together to serve as an elevator. The hori-
zontal tail also may be used. for longitudinal control by linking it to
the stick as an all-movable surface or by varying the angle of attack of
a free-floating tail with a servotab. The method of analysis of the
data is quite different, depending.on which of these two uses is made of
the horizontal tail. The discussion of the longitudinal stability and
control characteristics of the model has been divided into two parts,
therefore, to separate the analysis of the data as applied to airplanes
using the horizontal tail for the two different purposes.
Horizontal Tail Used to Overcome Change in Stability
W
When the horizontal tail is used simply as a device to overcome
the change in stability between subsonic and supersonic speeds, it isw~lmmae
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Bates, William R. Low-speed static longitudinal stability characteristics of a canard model having a 60 degrees triangular wing and horizontal tail, report, November 9, 1949; (https://digital.library.unt.edu/ark:/67531/metadc58302/m1/4/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.