If you only care about efficiency, you want the one that has the highest Cl/Cd at the design angle of attack, which may not not zero. Determine desired Cl using required lift (weight plus tail download) in the following:
L = Cl * A * .5 * r * V^2
where L is lift, Cl is coefficient of lift, A is wing area, r is density and V is Velocity. Explanation is at:
https://www.grc.nasa.gov/www/k-12/airplane/lifteq.html
Look through your charts for AoA at that Cl then pick the one with the highest CL/Cd at the associated AoA.