Max thickness: 7.0% at x = 24.75% chord
Max camber: 7.0% at x = 35.77% 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.
F1A. Airfoil 7% thick, 7% camb, for Clmax>1.6 at Re 100k,with trip top at 10% chord (also good from Re 60k).