Canard surface role estimation for aircraft of the canard layout

The range of subsonic speeds is considered. The research of interference of the front and rear load-bearing surfaces is focused on the assessment of two factors: the degree of lift increasing of the wing-canard system due to the positive canard surface lift force and the role of this force in the total normal force. The discrete vortex method is used. The analysis is carried out for the wing and the canard surface of a rectangular shape. The pitch of the span division is assumed to be the same for the canard surface and wing. This allows us to avoid distortion of the results obtained. All wing and tail panels are considered as a unified vortex system, and the position of the calculated points is determined in a single reference plane. The vertical displacement of the vortex descending from the canard surface relative to the wing is taken into account. A single system of equations is formed. The difference in the angles of attack of the canard surface and wing is taken into account. The distribution of the lift load along the wingspan is analyzed. The values of the coefficients of lift force for the isolated wing and for the wing, taking into account interference with the canard surface, are determined. This is reflected both in the magnitude of the lift force generated by the wing and in the wing’s contribution to the overall normal force of the wing-canard system. A strong influence of the relative wingspan of the empennage on the distribution of lift force over the wingspan is noted. At the same time, the aerodynamic layout acquires the characteristics of a “rotary wing” scheme. It has also been established that in all cases studied, the empennage makes a significant contribution to the total normal force. 

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