Select an airfoil that maximises this value at the calculated optimum lift coefficient. Energy means potential energy in this case $E_$ doesn't matter). Your definition of efficiency is minimum energy loss. Since this is for gliders, the answer will be quite simple. However, if you also care about handling, leave some margin at the outer wing in order to have stall start first at the root. Adjust taper and twist until you reach this result (and subtract the twist from the differences in the airfoil's zero-lift angle to arrive at your geometric twist distribution). (Questions 5-7) With some algebraic analysis, find the effects of Airspeed. This should maximise the lift from that wing. The precise answer normally depends on your means of propulsion. The relationship between airfoil thickness is the greater the thickness, the greater the CLmax and AOA are. But your common sense is correct in predicting that this will be a slow airplane. The $\alpha$=0 point on the polar would be a poor metric - there is nothing special about it, and your aircraft will not fly at this polar point when you strive for longest endurance.
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