Wing/Tail Analysis Program

This Java application computes trimmed performance of a wing and canard or tail. Enter the parameters in the text boxes below, then drag the tail forward or aft, even make it a canard, and watch how the required tail load and induced drag change. The flow is from left to right.

Details:
The calculations assume that there is no section pitching moment,that each surface is individually elliptically-loaded, and that there is no vertical gap between the surfaces. The static margin is based on a reference chord defined here as the total (wing+tail) area divided by the wing span.