The Airplane Lift

The lift of airplanes is given by the following conventional equations:o the particle \begin{equation} L = \frac{1}{2} \rho V^2 S \, C_{L} \label{eq:Lift:Equation} \end{equation}

Typical airfoil section.
Typical airfoil section.
Airfoil designs.
Airfoil designs.
Airfoil pressure distribution at normal angles of attack.
Airfoil pressure distribution at normal angles of attack.
Airfoil pressure distribution at high angles of attack.
Airfoil pressure distribution at high angles of attack.
Airfoil pressure distribution at low angles of attack.
Airfoil pressure distribution at low angles of attack.
The horse-shoe vortex representing the wing in classical aerodynamic theory.
The horse-shoe vortex representing the wing in classical aerodynamic theory.
The horse-shoe vortex representing the wing in classical aerodynamic theory.
The horse-shoe vortex representing the wing in classical aerodynamic theory.
The downwash behind a wing, at the horizontal tailplane.
The downwash behind a wing, at the horizontal tailplane.
The downwash behind a wing, at the horizontal tailplane.
The downwash behind a wing, at the horizontal tailplane.