I'm in the process of designing a flying wing. I'm trying to keep it a small as possible, so the lift coefficient is very crucial for me. I'm currently looking at some airfoils but most of them deliver the good Cl at AOA larger than 0.
When deciding a lift coefficient --let's assume 0.5,-- should I choose an airfoil that provides me with a Cl of 0.5 at 0 AOA?
When the flying wing is cruising, the lift force needs to equal the weight, but does the flying wing cruise at 0 AOA or can it cruise at 3° of AOA so it can it can keep its altitude?