NACA M12 (nacam12-il)
NACA M12 - NACA M12 airfoil
| Details | Dat file | Parser | |
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(nacam12-il) NACA M12 NACA M12 airfoil Max thickness 11.9% at 30% chord. Max camber 2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA M12 1.0000 0.0020 0.9500 0.0107 0.9000 0.0189 0.8000 0.0350 0.7000 0.0498 0.6000 0.0627 0.5000 0.0725 0.4000 0.0786 0.3000 0.0795 0.2000 0.0730 0.1500 0.0661 0.1000 0.0559 0.0750 0.0489 0.0500 0.0401 0.0250 0.0286 0.0125 0.0203 0.0000 0.0000 0.0125 -0.0165 0.0250 -0.0214 0.0500 -0.0272 0.0750 -0.0307 0.1000 -0.0331 0.1500 -0.0300 0.2000 -0.0380 0.3000 -0.0398 0.4000 -0.0396 0.5000 -0.0382 0.6000 -0.0350 0.7000 -0.0300 0.8000 -0.0231 0.9000 -0.0137 0.9500 -0.0081 1.0000 -0.0020 |
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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 M12 (nacam12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacam12-il | 50,000 | 9 | 31.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 50,000 | 5 | 33.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 100,000 | 9 | 49.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 100,000 | 5 | 48.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 200,000 | 9 | 66.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 200,000 | 5 | 56.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 500,000 | 9 | 71.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 500,000 | 5 | 62.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 1,000,000 | 9 | 78.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 1,000,000 | 5 | 71.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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