NACA65-615 a=0.6

NACA65615a=0.6
DB Name: NACA65-615 a=0.6
Family: NACA 65-series
Max thickness: 15.0% at x = 39.76% chord
Max camber: 4.0% at x = 47.92% 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