Vertical Tail Angle Of Attack Given By Tail Side Force Calculator

The Vertical Tail Angle of Attack refers to the angle between the chord line of the vertical tail (fin) of an aircraft and the local relative wind. This angle is crucial in aerodynamics as it influences the lift and, consequently, the yawing moment generated by the vertical tail. Adjusting the vertical tail angle of attack is a means of controlling the aircraft’s yawing motion, stability, and directional control during flight. The formula to calculate Vertical Tail Angle of Attack as follows:

Where:

• Y_v is the Vertical tail side force in N.
• C_v is the Vertical tail lift curve slope in 1/rad.
• Q_v is the Dynamic pressure of Tail in Pa.
• S_v is the Vertical Tail Area in m²
• α_v is the Vertical Tail Angle of Attack in radian.