The wing is divided into the number of panels you select, up to 120. The inertia loads for the wing are included in the calculations.
Output is plotted versus span.
The flight envelope can be investigated for structural loads, and the stalling characteristics of the wing are readily visualized. The picture below shows the flight envelope, and provides the Cl and speed needed to run all of the important flight conditions of your airplane. The following is a run using 4 chordwise and 20 spanwise panels. It is being run at 47.40 mph at a Cl of 1.5. The output indicates a wing root bending moment from lift of 56,071 in.