NACA65-610 a=0.8

NACA65610a=0.8
DB Name: NACA65-610 a=0.8
Family: NACA 65-series
Max thickness: 10.0% at x = 41.75% chord
Max camber: 3.9% at x = 51.97% 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