The vertical tail lift curve slope in flight mechanics is a parameter that characterizes how the side force generated by the vertical tail changes with variations in sideslip angle. It signifies the effectiveness of the vertical tail in producing lateral forces to control yawing motion and maintain stability during aircraft flight. The formula to calculate Vertical tail Curve slope as follows:
Where:
- Yv is the Vertical tail side force in N,
- αv is the Vertical tail angle of attack in radian,
- Qv is the Dynamic pressure of Vertical tail in Pa,
- Sv is the vertical tail area in m2.