Yawing moment coefficient for given vertical tail lift curve slope Calculator

The Yawing moment coefficient for given vertical tail lift curve slope is a moment that lends to rotate an airplane about its vertical axis yawing moment is positive when it tends to turn the plane to the right and negative when it turns the plane to the left and is represented as C_n = 𝒍_v*S_v*Q_v*C_v*(β+σ)/(S*b*Q_w) or Yawing moment coefficient = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Wing dynamic pressure). The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft, The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind, Sidewash angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.