NACA M2 AIRFOIL (m2-il)
NACA M2 AIRFOIL - NACA/Munk M-2 airfoil
| Details | Dat file | Parser | |
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(m2-il) NACA M2 AIRFOIL NACA/Munk M-2 airfoil Max thickness 8% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M2 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0130000
0.0250000 0.0174000
0.0500000 0.0233000
0.1000000 0.0284000
0.1500000 0.0318000
0.2000000 0.0349000
0.2500000 0.0378000
0.3000000 0.0400000
0.4000000 0.0400000
0.5000000 0.0374000
0.6000000 0.0330000
0.7000000 0.0271000
0.8000000 0.0199000
0.9000000 0.0115000
0.9500000 0.0060000
1.0000000 0.0020000
0.0000000 0.0000000
0.0125000 -.0130000
0.0250000 -.0174000
0.0500000 -.0233000
0.1000000 -.0284000
0.1500000 -.0318000
0.2000000 -.0349000
0.2500000 -.0378000
0.3000000 -.0400000
0.4000000 -.0400000
0.5000000 -.0374000
0.6000000 -.0330000
0.7000000 -.0271000
0.8000000 -.0199000
0.9000000 -.0115000
0.9500000 -.0060000
1.0000000 -.0020000
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Polars for NACA M2 AIRFOIL (m2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m2-il | 50,000 | 9 | 21.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 50,000 | 5 | 21.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 100,000 | 9 | 29.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 100,000 | 5 | 27.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 200,000 | 9 | 32 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 200,000 | 5 | 36.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 500,000 | 9 | 45.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 500,000 | 5 | 54.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 1,000,000 | 9 | 60.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 1,000,000 | 5 | 70.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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