NACA M20 AIRFOIL (m20-il)
NACA M20 AIRFOIL - NACA/Munk M-20 airfoil
| Details | Dat file | Parser | |
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(m20-il) NACA M20 AIRFOIL NACA/Munk M-20 airfoil Max thickness 8.2% at 30% chord. Max camber 6.1% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M20 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0170500
0.0250000 0.0260000
0.0500000 0.0417000
0.0750000 0.0537000
0.1000000 0.0647000
0.1500000 0.0803000
0.2000000 0.0914000
0.3000000 0.1021000
0.4000000 0.0999000
0.5000000 0.0892000
0.6000000 0.0730000
0.7000000 0.0540000
0.8000000 0.0350000
0.9000000 0.0178000
0.9500000 0.0106000
1.0000000 0.0047000
0.0000000 0.0000000
0.0125000 -.0097500
0.0250000 -.0094000
0.0500000 -.0057000
0.0750000 -.0013000
0.1000000 0.0031000
0.1500000 0.0103000
0.2000000 0.0156000
0.3000000 0.0206000
0.4000000 0.0190000
0.5000000 0.0133000
0.6000000 0.0058000
0.7000000 -.0012000
0.8000000 -.0055000
0.9000000 -.0056000
0.9500000 -.0036000
1.0000000 0.0000000
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Polars for NACA M20 AIRFOIL (m20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m20-il | 50,000 | 9 | 10.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 50,000 | 5 | 26.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 100,000 | 9 | 55.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 100,000 | 5 | 56.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 200,000 | 9 | 78.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 200,000 | 5 | 78 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 500,000 | 9 | 108.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 500,000 | 5 | 105.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 9 | 131.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 5 | 125.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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