NACA66-712 a=0.5

NACA66712a=0.5
DB Name: NACA66-712 a=0.5
Family: NACA 66-series
Max thickness: 12.0% at x = 45.85% chord
Max camber: 4.9% at x = 43.82% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
XFOIL ncrit=9
XFOIL ncrit=5
XFOIL ncrit=12
NF ncrit=5
NF ncrit=9
NF ncrit=12

Notes:

Coordinates generated by JavaFoil
NeuralFoil data computed using Peter Sharpe's NeuralFoil: An airfoil aerodynamics analysis tool using physics-informed machine learning, 2023, GitHub repository: https://github.com/peterdsharpe/NeuralFoil. Version 0.3.1 xxxlarge