Hi, I am trying to find a NACA-aerofoil for a given wing geometry (AR = 8, Taper: 0.35, Cruise CL = 0.05 at 0.6 degrees angle). Do any of you know if it is possible to find an aerofoil that will give this wing the best L/D-ratio at this cruise AoA (0.6 deg)? I have done some analysis on several aerofoils on my wing using the XFLR5-software, but the best L/D-drag is usually achieved at an angle of attack of 3-4 degrees. Or maybe the only solution would be to change the wing geometry? The cruise lift coefficient of 0.05 is very small, but due to some geometrical problems this can maximum be set to 0.1, giving an AR of 5. But even at this CL, I struggle to find the aerofoil giving the best L/D-ratio, or at least very close to it. Hope someone can help me out with this.