The change in the aircraft’s pitching moment coefficient (Cm) due to the deflection of the control surface calculator

The change in the aircraft’s pitching moment coefficient (Cm) due to the deflection of a control surface, often denoted as Cmδe, represents how the aircraft’s pitching moment (nose-up or nose-down tendency) changes when a specific control surface, such as an elevator or stabilator, is deflected. In flight mechanics and aircraft stability and control analysis, this parameter is essential for understanding how control inputs affect the aircraft’s pitch behavior.

  • Cmδe: This represents the change in the aircraft’s pitching moment coefficient (Cm) due to the deflection of the control surface (δe). It quantifies how the aircraft’s pitch behavior changes when the control surface is moved.
  • η: This parameter represents an efficiency factor or other factors affecting the control surface’s effectiveness.
  • CLαt: This represents the derivative of lift with respect to the angle of attack (α) for the entire aircraft or the tail section. It characterizes how the lift force changes with variations in angle of attack.
  • τ: This may represent the control surface deflection angle or the control input. It is typically measured in radians or degrees.
  • -Vh means tail volume ratio

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