Yawing Moment Coefficient given Rudder Deflection Calculator

The Yawing Moment Coefficient given Rudder Deflection formula is defined as the generation of a yaw moment, which is a rotational force around the aircraft's vertical axis. This moment causes the aircraft to yaw (turn its nose) left or right. The pilot controls the yaw moment by deflecting the rudder, a hinged surface on the vertical stabilizer and is represented as C_n = -(Q_v/Q_w)*((l_v*S_v)/(b*s))*(d_cl/dδ_r)*δ_r or Yawing Moment Coefficient = -(Dynamic Pressure at Vertical Tail/Dynamic Pressure at Wing)*((Distance between Rudder Hinge Line and Cg*Vertical Tail Area)/(Wingspan*Wing Reference Area))*(Coefficient of lift/Deviated Rudder Deflection Angle)*Rudder Deflection Angle. The Dynamic Pressure at Vertical Tail of an aircraft is the pressure exerted by the air flowing past the tail due to the aircraft's forward motion, Dynamic Pressure at Wing Represents the kinetic energy per unit volume of air due to its motion, Distance between Rudder Hinge Line and Cg is the geometric property which define the moment arm of the rudder force, affecting the overall yawing moment produced, The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, Wing Reference Area is the planform area, refers to the projected area of the wing, as if viewed directly from above, Coefficient of lift is a dimensionless quantity that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity, and an associated reference area, Deviated Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw & Rudder Deflection Angle is a lateral force and hence a bigger yawing moment (N), leading to a more pronounced yaw.