I also agree.

Having the lift coefficient curve shown in post #6, it is not difficult to make an estimate of the wing angle for regular level flight.
Nothing too exact, but better than a blind guess.

CL = (64.4 * weight in pounds) / (0.075 * (cruise velocity in ft/s)^2 * wing area in sqft)

For my 0.40 planes with wingload of 20 ounces/sqft, I have calculated CL = 0.14 ~ 0.17

Consider that washout will reduce the AOA towards the tip, hence the CL value.

This thread explains typical CL values for RC models:

http://www.rcuniverse.com/forum/m_87...tm.htm#8704122

Downthust may not be necessary, but some right thrust always helps with taildraggers.