Rolling moment coefficient Calculator

The rolling moment coefficient (Cl_p​​) is a dimensionless aerodynamic parameter that characterizes the tendency of an aircraft to roll in response to a change in roll rate. It is a key aspect of an aircraft’s lateral stability and control. A positive Cl_p​​ indicates that an increase in roll rate leads to an additional rolling moment in the same direction, contributing to lateral stability. On the other hand, a negative Cl_p​​ suggests an opposite effect. The formula to calculate Rolling moment Coefficient as follows :

Where:

• Cl_p​​ is the rolling moment coefficient with respect to roll rate.
• L_p​ is the rolling moment in Nm
• $\rho$ is the air density in kg/m³
• $V$ is the airspeed of the aircraft (m/s).
• $S$ is the wing area (in m²).
• $b$ is the wingspan (in m).