NACA 16-012 (naca16012-il)
NACA 16-012 - NACA 16-012 airfoil
| Details | Dat file | Parser | |
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(naca16012-il) NACA 16-012 NACA 16-012 airfoil Max thickness 12% at 50% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 16-012 1.0000 0.00120 0.9500 0.01415 0.9000 0.02517 0.8000 0.04199 0.7000 0.05269 0.6000 0.05835 0.5000 0.06000 0.4000 0.05855 0.3000 0.05417 0.2000 0.04664 0.1500 0.04135 0.1000 0.03457 0.0750 0.03032 0.0500 0.02509 0.0250 0.01805 0.0125 0.01292 0.0000 0.00000 0.0125 -0.01292 0.0250 -0.01805 0.0500 -0.02509 0.0750 -0.03032 0.1000 -0.03457 0.1500 -0.04135 0.2000 -0.04664 0.3000 -0.05417 0.4000 -0.05855 0.5000 -0.06000 0.6000 -0.05835 0.7000 -0.05269 0.8000 -0.04199 0.9000 -0.02517 0.9500 -0.01415 1.0000 -0.00120 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA 16-012 (naca16012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca16012-il | 50,000 | 9 | 21.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 50,000 | 5 | 22.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 100,000 | 9 | 28.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 100,000 | 5 | 30.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 200,000 | 9 | 44.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 200,000 | 5 | 32.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 500,000 | 9 | 42.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 500,000 | 5 | 44.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 1,000,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 1,000,000 | 5 | 55.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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