NACA 0018 (naca0018-il)
NACA 0018 - NACA 0018 airfoil
| Details | Dat file | Parser | |
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(naca0018-il) NACA 0018 NACA 0018 airfoil Max thickness 18% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 0018 1.0000 0.00189 0.9500 0.01210 0.9000 0.02172 0.8000 0.03935 0.7000 0.05496 0.6000 0.06845 0.5000 0.07941 0.4000 0.08705 0.3000 0.09003 0.2500 0.08912 0.2000 0.08606 0.1500 0.08018 0.1000 0.07024 0.0750 0.06300 0.0500 0.05332 0.0250 0.03922 0.0125 0.02841 0.0000 0.00000 0.0125 -0.02841 0.0250 -0.03922 0.0500 -0.05332 0.0750 -0.06300 0.1000 -0.07024 0.1500 -0.08018 0.2000 -0.08606 0.2500 -0.08912 0.3000 -0.09003 0.4000 -0.08705 0.5000 -0.07941 0.6000 -0.06845 0.7000 -0.05496 0.8000 -0.03935 0.9000 -0.02172 0.9500 -0.01210 1.0000 -0.00189 |
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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 0018 (naca0018-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0018-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 5 | 26.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 9 | 37.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 5 | 38.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 9 | 50.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 5 | 48 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 9 | 65.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 5 | 61.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 9 | 77.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 5 | 73.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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