Thanks!
Your notes were most helpful, Johng.
I did the math again(Re=p.v.L/u): With a 12in chord (AR= 6.7) at 17m/s (38mph), I'd have Re around 300k - with a straight form.
Is the 6.7 Aapect Ratio too low for this application?
Maybe I could go the Cessna way and taper it half way the span to, say, 6in (here's our Re 150k), but that would certainly prohibit the external airfoil flap option, though.
What about those lift coeficients of 4.81 for the LI74?!?!!! Where do I read more about it?
Thanks again!