The horizontal stabilizer, also known as the tailplane or horizontal tail, is an essential component of an aircraft’s design used to control its pitch and maintain stability in the longitudinal axis. The key parameter for the horizontal stabilizer is often its lift coefficient (Cl).
The formula for calculating the lift coefficient (Cl) of the horizontal stabilizer is as follows:
- Cl is the lift coefficient for the horizontal stabilizer, a dimensionless quantity.
- Lh is the lift force generated by the horizontal stabilizer, measured in Newtons (N).
- ρ is the air density, measured in kilograms per cubic meter (kg/m³).
- V is the velocity of the aircraft, measured in meters per second (m/s).
- Sh is the reference area of the horizontal stabilizer, measured in square meters (m²).