Aircraft lift coefficient
by gowtham[ Edit ] 2010-02-16 19:06:06
The lift coefficient (CL or CZ) is a dimensionless coefficient that relates the lift generated by an airfoil, the dynamic pressure of the fluid flow around the airfoil, and the planform area of the airfoil. It may also be described as the ratio of lift pressure to dynamic pressure
Aircraft lift coefficient
Lift coefficient may be used to relate the total lift generated by an aircraft to the total area of the wing of the aircraft. In this application it is called the aircraft lift coefficient CL.
The lift coefficient CL is equal to:[3][2]
C_L={L \over \frac{1}{2}\rho v^2A} = \frac{L}{q A}
where
* L is the lift force,
* ρ is fluid density,
* v is true airspeed,
* q is dynamic pressure, and
* A is planform area.
The lift coefficient is a dimensionless number.
The aircraft lift coefficient can be approximated using the Lifting-line theory
