NACA M6 (nacam6-il)
NACA M6 - NACA M6 airfoil
| Details | Dat file | Parser | |
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(nacam6-il) NACA M6 NACA M6 airfoil Max thickness 12% at 30% chord. Max camber 2.1% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA M6 1.0000 0.0026 0.9500 0.0088 0.9000 0.0155 0.8000 0.0306 0.7000 0.0458 0.6000 0.0603 0.5000 0.0726 0.4000 0.0805 0.3000 0.0822 0.2500 0.0801 0.2000 0.0755 0.1500 0.0682 0.1000 0.0571 0.0750 0.0494 0.0500 0.0403 0.0250 0.0281 0.0125 0.0197 0.0000 0.0000 0.0125 -0.0176 0.0250 -0.0220 0.0500 -0.0273 0.0750 -0.0303 0.1000 -0.0324 0.1500 -0.0347 0.2000 -0.0362 0.2500 -0.0371 0.3000 -0.0379 0.4000 -0.0390 0.5000 -0.0394 0.6000 -0.0382 0.7000 -0.0348 0.8000 -0.0283 0.9000 -0.0177 0.9500 -0.0108 1.0000 0.0026 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for NACA M6 (nacam6-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacam6-il | 50,000 | 9 | 30.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 50,000 | 5 | 32.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 100,000 | 9 | 49.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 100,000 | 5 | 49.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 200,000 | 9 | 67.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 200,000 | 5 | 64.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 500,000 | 9 | 89.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 500,000 | 5 | 72.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 1,000,000 | 9 | 90.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 1,000,000 | 5 | 81 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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