Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: lateral-directional characteristics of a triangular wing and canard Page: 4 of 78
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NACA RM A57TL8 3
Swing area formed by extending the leading and trailing edges to the
plane of symmetry, sq ft
a, angle of attack of wing root chord, deg
3 sideslip angle measured between relative wind and vertical plane of
6 angle of deflection of the canard with respect to the extended wing
chord plane, positive when trailing edge is down, deg
Configurations are denoted by the following letters used in combina-
V vertical tail
APPARATUS AND MODEL
The experimental data were obtained in the Ames 6- by 6-foot super-
sonic wind tunnel which is a closed-circuit variable-pressure type with
a Mach number range continuous from 0.70 to 2.22. A recent modification
involved perforating the test-section floor and ceiling and adding a
boundary-layer removal system to enable uniform flow to be maintained at
transonic and low supersonic speeds. At the same time injector flaps
were installed downstream of the test section to extend the upper Mach
number limit by reducing the re quired compression ratio across the nozzle
and by better matching the weight flow characteristics of the nozzle with
those of the compressor.
Analysis of the results of an extensive survey of the modified wind-
tunnel characteristics, although incomplete, is sufficiently complete to
establish the validity of the results of the present investigation.
Description of Model and Balance
The sting-mounted model (fig. 1(a)) consisted of an aspect ratio 2.0
triangular wing, an aspect ratio 2.0 movable triangular canard, and a low
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Peterson, Victor L. & Menees, Gene P. Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: lateral-directional characteristics of a triangular wing and canard, report, March 4, 1958; (digital.library.unt.edu/ark:/67531/metadc63930/m1/4/: accessed March 18, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.