Change in moment (torque) around the longitudinal axis calculator

The change in moment (torque) around the aircraft’s longitudinal axis, often referred to as the “roll axis,” is related to the aerodynamic behavior of an aircraft’s roll due to changes in angle of attack and other parameters. 

• Mw​ is the change in moment around the longitudinal axis (newton-meter, N·m).
• $Q$ is the dynamic pressure (pascals, Pa).
• $S$ is the reference area of the aircraft (square meters, m²).
• $c$ is the mean aerodynamic chord length (meters, m).
• u0​ is the equilibrium velocity (meters per second, m/s).
• Iyy​ is the moment of inertia around the longitudinal axis (kilogram-square meters, kg·m²).
• Cmα​ is the coefficient of pitching moment with respect to angle of attack $\alpha$.