Abstract
This paper presents the results of numerical studies of the effect of horizontal canard installation in a maneuverable aircraft model with a sharp-edged forebody, which smoothly turns into the leading edge extension, on the longitudinal aerodynamic characteristics at low subsonic speeds (M = 0.15) within the range of angles of attack α = 0°–35° using the two-parameter k-ω shear stress transport turbulence model with empirical correction for the streamline curvature. The results of the numerical calculations are in satisfactory agreement with the experimental data obtained in the T-102 wind tunnel at TsAGI within the entire range of the angles of attack. Based on the numerical and experimental studies, it is shown that installation of a horizontal canard has a positive effect on the aerodynamic characteristics of the maneuverable aircraft model at rather high angles of attack (α > 19°). The positive effect of the horizontal canard installation is mainly due to the influence of the vortex structures generated from the sharp-edged forebody on the trajectory, which yields favorable interference of the forebody and wing vortices.
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