Hey Banktoturn!
Thanks for the info. I've never even seen a Cd for a model airplane so I have no clue what to expect but you've confirmed my hunch in which case the Terminal Dive idea is just not going to work for the Duellist.

I have to admit my only drag experience is with full size cars and that was a long time ago. I assumed frontal area and projected area were the same thing for parasitic drag purposes.

The way I found area for the wing was by finding the largest cross-sectional area of the wing panel perpendicular to the airflow. I found the thickest point of the root rib, added skin thickness and multiplied that number by the length of the panel. I then subtracted a triangular area to compensate for change in thickness from root to tip. Is this incorrect? How should I do it?