NACA M2 (nacam2-il)
NACA M2 - NACA M2 airfoil
| Details | Dat file | Parser | |
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(nacam2-il) NACA M2 NACA M2 airfoil Max thickness 8.1% 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 M2 1.0000 0.0020 0.9500 0.0069 0.9000 0.0115 0.8000 0.0199 0.7000 0.0271 0.6000 0.0330 0.5000 0.0374 0.4000 0.0400 0.3000 0.0403 0.2000 0.0378 0.1500 0.0349 0.1000 0.0305 0.0750 0.0274 0.0500 0.0233 0.0250 0.0174 0.0125 0.0130 0.0000 0.0000 0.0125 -0.0130 0.0250 -0.0174 0.0500 -0.0233 0.0750 -0.0274 0.1000 -0.0305 0.1500 -0.0349 0.2000 -0.0378 0.3000 -0.0403 0.4000 -0.0400 0.5000 -0.0374 0.6000 -0.0330 0.7000 -0.0271 0.8000 -0.0199 0.9000 -0.0115 0.9500 -0.0069 1.0000 -0.0020 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA M2 (nacam2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacam2-il | 50,000 | 9 | 25.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 50,000 | 5 | 23.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 100,000 | 9 | 33.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 100,000 | 5 | 27.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 200,000 | 9 | 38.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 200,000 | 5 | 36.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 500,000 | 9 | 44.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 500,000 | 5 | 54.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam2-il | 1,000,000 | 9 | 60.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam2-il | 1,000,000 | 5 | 70.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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