NACA M21 AIRFOIL (m21-il)
NACA M21 AIRFOIL - NACA/Munk M-21 airfoil
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(m21-il) NACA M21 AIRFOIL NACA/Munk M-21 airfoil Max thickness 12% at 30% chord. Max camber 6% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M21 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0221000
0.0250000 0.0336000
0.0500000 0.0518000
0.0750000 0.0662000
0.1000000 0.0782000
0.1500000 0.0965000
0.2000000 0.1090000
0.3000000 0.1202000
0.4000000 0.1178000
0.5000000 0.1055000
0.6000000 0.0868000
0.7000000 0.0649000
0.8000000 0.0421000
0.9000000 0.0202000
0.9500000 0.0105000
1.0000000 0.0024000
0.0000000 0.0000000
0.0125000 -.0151000
0.0250000 -.0186000
0.0500000 -.0185000
0.0750000 -.0149700
0.1000000 -.0113000
0.1500000 -.0065000
0.2000000 -.0026000
0.3000000 0.0007000
0.4000000 -.0011000
0.5000000 -.0057000
0.6000000 -.0114000
0.7000000 -.0156000
0.8000000 -.0165000
0.9000000 -.0127000
0.9500000 -.0087000
1.0000000 -.0024000
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Polars for NACA M21 AIRFOIL (m21-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m21-il | 50,000 | 9 | 5.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 50,000 | 5 | 22.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 100,000 | 9 | 29.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 100,000 | 5 | 48.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 200,000 | 9 | 70.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 200,000 | 5 | 73.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 500,000 | 9 | 107.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 500,000 | 5 | 105.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m21-il | 1,000,000 | 9 | 135.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m21-il | 1,000,000 | 5 | 128.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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