NACA67-120 a=0.8

NACA67120a=0.8
DB Name: NACA67-120 a=0.8
Family: NACA 67-series
Max thickness: 20.0% at x = 47.85% chord
Max camber: 0.5% at x = 51.95% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
XFOIL ncrit=9
XFOIL ncrit=12
XFOIL ncrit=5
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