NACA M12 AIRFOIL (m12-il)
NACA M12 AIRFOIL - NACA/Munk M-12 airfoil
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(m12-il) NACA M12 AIRFOIL NACA/Munk M-12 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 Lednicer format |
NACA M12 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0203300
0.0250000 0.0286500
0.0500000 0.0403000
0.0750000 0.0490500
0.1000000 0.0561000
0.1500000 0.0666000
0.2000000 0.0734000
0.3000000 0.0801000
0.4000000 0.0794000
0.5000000 0.0735000
0.6000000 0.0639000
0.7000000 0.0512000
0.8000000 0.0366000
0.9000000 0.0207000
0.9500000 0.0126000
1.0000000 0.0040000
0.0000000 0.0000000
0.0125000 -.0164800
0.0250000 -.0213500
0.0500000 -.0271000
0.0750000 -.0305500
0.1000000 -.0329000
0.1500000 -.0357000
0.2000000 -.0376000
0.3000000 -.0392000
0.4000000 -.0388000
0.5000000 -.0372000
0.6000000 -.0338000
0.7000000 -.0286000
0.8000000 -.0215000
0.9000000 -.0119000
0.9500000 -.0062000
1.0000000 0.0000000
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Polars for NACA M12 AIRFOIL (m12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m12-il | 50,000 | 9 | 31.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 50,000 | 5 | 33.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 100,000 | 9 | 49 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 100,000 | 5 | 48.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 200,000 | 5 | 62.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 500,000 | 9 | 86.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 500,000 | 5 | 77.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 9 | 98.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 5 | 85.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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