Max thickness: 10.1% at x = 41.73% chord
Max camber: 1.3% at x = 45.80% 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.
Designed for pylon racing model aircraft (FAI class F3D, Q-40 and similar).
Moment coefficient cm c/4 = -0.0329.
Numerically optimized for Reynolds numbers between 250k and 1.5M.
Well suited for a flap of 20% chord length.
Requires good construction methods to achieve laminar flow up to 80% of the chord length.
Turbulators at 80% chord on the both sides should be used for Reynolds numbers between 500k and 1M.