Solving for the pitching moment damping coefficient of aircraft canard surface

Canards are basically horizontal tail installed ahead of centre of gravity which makes aircraft to pitch up or pitch down with the help of moving parts of canard surface. In canards, configuration point of lift on the wing is behind the centre of gravity of the aircraft. To adjust the characteristic nose down inclination, the canard produces an upward lifting power which opposes weight. It also makes airplane unstable if wind gust increases its angle of attack. In some cases wing lift occurs because of increase in angle of attack. In this work an analytical method has been used to evaluate the pitch damping coefficient for the canard surface of an aircraft. The method is appropriate for a typical aircraft with canard surface. This expression is extracted out by evaluating the moment added to the pitching moment because of the change in the lift of the canard surface. No estimations of physical parameters were useful on the grounds that the primary objective is to find out the expression. The results show that the damping ability is similar as that of the tail. The significance of this particular work is to develop an expression for damping coefficient. The pitch rate causes effective increase in wing angle of the attack resulting in more lift. If the canard's lift is greater than the wing, the nose will pitch further up and hence longitudinal stability of aircraft is more than steady flight condition.