Max thickness: 8.0% at x = 30.06% chord
Max camber: 0.4% at x = 35.76% 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.
Very low drag coefficient airfoil for high speed model aircraft
The ideal Reynoldsnumber is about 1'300'000.
Ideal chord length about c[m] = 67 / v[km/h].
more maximum lift than MH 50.