I'm sorry, I wasn't very clear. The area used for Cd is the planform area of the wing, rather than the frontal area. That is, the area as seen from the top of the plane, not the front.
banktoturn
ORIGINAL: CrateCruncher
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?