lift coefficient during climb refers to the coefficient of lift () associated with an aircraft’s performance in a climbing maneuver. The lift coefficient quantifies the amount of lift generated by an aircraft’s wings relative to the dynamic pressure of the airflow around them.
Clc=w*cos ( γ)/(o.5**v*s)
- : This represents the lift coefficient during climb. It quantifies the lift generated by the aircraft’s wings relative to dynamic pressure, wing area, and the aircraft’s weight distribution due to the angle of climb.
- : This likely represents the aircraft’s weight.
- : This could represent the flight path angle, which is the angle between the aircraft’s velocity vector and the horizontal plane.
- : This is the air density.
- : This represents the aircraft’s velocity (airspeed).
- : This represents the wing area.