NACA 4412 (naca4412-il)
NACA 4412 - NACA 4412 airfoil
| Details | Dat file | Parser | |
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(naca4412-il) NACA 4412 NACA 4412 airfoil Max thickness 12% at 30% chord. Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 4412 1.0000 0.0013 0.9500 0.0147 0.9000 0.0271 0.8000 0.0489 0.7000 0.0669 0.6000 0.0814 0.5000 0.0919 0.4000 0.0980 0.3000 0.0976 0.2500 0.0941 0.2000 0.0880 0.1500 0.0789 0.1000 0.0659 0.0750 0.0576 0.0500 0.0473 0.0250 0.0339 0.0125 0.0244 0.0000 0.0000 0.0125 -0.0143 0.0250 -0.0195 0.0500 -0.0249 0.0750 -0.0274 0.1000 -0.0286 0.1500 -0.0288 0.2000 -0.0274 0.2500 -0.0250 0.3000 -0.0226 0.4000 -0.0180 0.5000 -0.0140 0.6000 -0.0100 0.7000 -0.0065 0.8000 -0.0039 0.9000 -0.0022 0.9500 -0.0016 1.0000 -0.0013 |
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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 4412 (naca4412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca4412-il | 50,000 | 9 | 33.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 50,000 | 5 | 36.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 9 | 56.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 5 | 76.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 9 | 107.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 5 | 101.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 9 | 129.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 5 | 119.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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