Max thickness: 15.3% at x = 30.19% chord
Max camber: 6.4% at x = 45.89% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
Coordinates from TraCFoil.
Commercial use of the airfoil may be restricted by the designer's copyright.
for very slow flying devices (modifications of the airfoil DAE11).
Airfoils are developed for Raynolds numbers from Re=300k up to Re=1M. In that range
lift is very high (CL up to 1.8), and drag is low. At Mid 405e, and at Re=500k power
factor is CL^1.5/CD=180, and CL/CD=142, both at about A0A=7 deg.