The yawing moment coefficient () is a measure of the aircraft’s response to sideslip (sideways airflow) and yawing motion. It indicates how the aircraft tends to rotate about its vertical axis (yaw axis) in response to yawing forces.
The equation represents the relationship between the yawing moment coefficient () of an aircraft and the contributions from its wing () and vertical tail ().
Here’s what each term means:
- : This is the yawing moment coefficient, which describes how the aircraft generates or responds to a yawing moment (a rolling motion due to yaw).
- : This term represents the yawing moment coefficient contribution from the aircraft’s wing. It accounts for the wing’s aerodynamic characteristics that affect yawing moments.
- : This term represents the yawing moment coefficient contribution from the aircraft’s vertical tail (vertical stabilizer). The vertical tail’s shape, size, and angle of attack influence its contribution to yawing moments.
The equation indicates that the overall yawing moment coefficient () is the sum of the yawing moment coefficients contributed by the wing () and the vertical tail (). This concept is central to the analysis of aircraft stability and control.
In the context of stability analysis, understanding the distribution of yawing moments between the wing and the vertical tail is important for assessing an aircraft’s ability to maintain coordinated flight, resist yawing motions, and respond to control inputs. The equation reflects the contribution of each component to the aircraft’s overall yawing behavior.
Keep in mind that the specific values of and would depend on the aircraft’s design, geometry, configuration, and other aerodynamic factors.