Cnpv: This is the yawing moment coefficient derivative with respect to sideslip angle (β) and roll rate (p). It describes how the aircraft’s yawing moment (the tendency to yaw or turn) changes as a result of changes in both sideslip angle (the angle between the aircraft’s velocity vector and longitudinal axis) and roll rate (the rate of change of roll angle).
- Cnpv: This represents the yawing moment derivative with respect to the sideslip angle (β) and the roll rate (p). In other words, it describes how the aircraft’s yawing moment (the tendency to yaw or turn) changes with changes in sideslip angle and roll rate.
- (-2/b^2): This is a constant factor in the equation.
- lv: This represents the lever arm of the vertical tail from the aircraft’s center of gravity (CG). It’s the distance between the CG and the vertical tail’s center of pressure.
- cos(α): This is the cosine of the angle of attack (α). The angle of attack is the angle between the oncoming air and the aircraft’s longitudinal axis.
- Zv: This represents the vertical tail’s lift curve slope.
- sin(α): This is the sine of the angle of attack (α).
- (Zv cos(α) – lv sin(α) / b): This is a term involving the product of the vertical tail’s lift curve slope, cosine of the angle of attack, lever arm of the vertical tail, and wingspan (b). It’s related to how the aircraft’s yawing moment is influenced by these factors.
- CyβV: This represents the lateral-directional stability derivative. It describes how the aircraft’s side force (Y) changes with changes in sideslip angle (β) and velocity