Panel procedure

The panel method is a method for the approximate calculation of the distribution of lift of a wing .

To do this, the wing is broken down into small elementary wings. A supporting vertebra is placed on each of these elementary wings along the 1/4 line. The strength of the eddies is then determined in such a way that the kinematic flow condition at the trailing edge is fulfilled. The kinematic flow condition is the "smooth" flow over the rear edge. Aerodynamic parameters can be determined from the resulting vortex distribution . These include lift, pitching moment and drag .