Investigation of Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback-Wing Airplane Model With Various Vertical Locations of Wing and Horizontal Tail: Static Longitudinal Stability and Control, M = 2.01 Page: 3 of 38
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NACA RM L551L06
INTRODUCTION
The experimentally determined effects of wing and tail position on
the aerodynamic characteristics of generalized aircraft configurations
can be of considerable usefulness to the designer in the estimation of
the stability and performance of similar specific configurations. In
addition, such generalized results may be useful in the verification of
various calculative methods for the prediction of the aerodynamic char-
acteristics of airplanes. A considerable amount of such experimental
data is available at low speeds (refs. 1 to 5, for example), wherein the
influence of both plan form and position of wings and tails has been
determined from wind-tunnel tests of models simulating high-speed type
aircraft. Similar investigations have been extended to high subsonic
Mach numbers (for example, refs. 5 to 9) and some results concerning the
effects of tail location on the longitudinal characteristics of some
rocket-propelled models have been obtained through the transonic speed
range (refs. 10 and 11). Only a limited amount of such experimental data
is available at present in the supersonic speed range. One example is
the investigation reported in reference 12 in which the effects of wing-
vertical location on the longitudinal characteristics of wing-body com-
binations were determined in the Mach number range from 0.61 to 0.91 and
from 1.20 to 1.90.
In order to provide additional results of general interest to the
designer for the supersonic speed range, an investigation has been con-
ducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach
number of 2.01 to determine the effects of wing-vertical location and
horizontal tail-vertical location on the longitudinal and lateral aero-
dynamic characteristics of a complete model having a 450 swept wing and
tail. The basic results, without analysis, are presented in reference 153.
An analysis of the effects of wing location and geometric dihedral for
the wing-body combination is presented in reference 14. This paper pre-
sents the static longitudinal stability and control characteristics at
M = 2.01 for the high-wing, mid-wing, and low-wing configurations, each
with four different vertical positions of the horizontal tail. In addi-
tion, results are presented for each tail position with the wing removed.
Several tail incidence angles in the range from 3.20 to -5.80 were
investigated.
SYMBOLS
The results are presented as standard NACA coefficients of forces
and moments. The data are referred to the stability axis system (fig. 1)
with the reference center of moments located at 25 percent of the wing
mean geometric chord.
a-I ~II II
2
I ol I imi IEN11 m am 1 11 1 I
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Spearman, M. Leroy & Driver, Cornelius. Investigation of Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback-Wing Airplane Model With Various Vertical Locations of Wing and Horizontal Tail: Static Longitudinal Stability and Control, M = 2.01, report, February 21, 1956; (https://digital.library.unt.edu/ark:/67531/metadc62064/m1/3/: accessed April 23, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.