Similar aircraft have a range of WCL which dictates their flight abilities. WCL equals the weight of your plane divided by the wing area multiplied by the square root of the wing area.

What do I mean? This value doesn't change with scale which means a full scale plane and model version of the same plane should have the same CWL if they want have the same flight characteristics. CWL is the responsible big brother of regular 2D wing loading. Congrats on making it this far! Last but not least is a little secret called the Cubic Wing Loading (CWL). Find this point for the main wing and stabilizers before continuing. This point is the Aerodynamic Center of the wing panel. Write this length down as it is important! With the GMC found, take 25% (1/4) of that distance from the leading edge and trace over to the root of the wing panel. Now measure the distance of the GMC as seen in the picture below. Draw a diagonal line from each end of the newly created lines and find where the two intersect. Next add the Root Chord (A) in front of and behind the Tip Chord (C). Take the lengths you found before and add the tip chord measure (C) in front of and behind the Root Chord (A). This method will work for most wings, tapered or not. Below is a graphical representation of how to find AC of a wing panel by using the Mean Aerodynamic Chord (MAC) or Geometric Mean Chord (GMC).

The AC is where all the aerodynamic forces act of the wing. With those dimensions and areas recorded we now move onto finding the Aerodynamic Center.

Steps to draw simple airplane