Ok,
For my project, I went looking for the design lift coefficients for the two extremes of the flight envelope:
1) Straight flight at maximum speed; approximately 300 mph.
2) Sustained 3 G turn decelerating to approx. 200 mph.
Aircraft weight: 725 lbs
Wing Area: 66 ft^2
Dynamic pressure calculated for standard conditions at 6,000 ft.
Using the lift equation: L = Cl X q X V
Where L = lift (weight), Cl = lift coefficient, q = dynamic pressure, and V = wing area
I came up with .0571 for condition #1 and .3856 for condition #2. Is there anything I'm not considering for the turn condition, if 3G is sustained, and the speed doesn't drop below 200 mph?