NACA-M1 AIRFOIL (m1-il)
NACA-M1 AIRFOIL - NACA/Munk M-1 airfoil
| Details | Dat file | Parser | |
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(m1-il) NACA-M1 AIRFOIL NACA/Munk M-1 airfoil Max thickness 6.2% 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-M1 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0103000
0.0250000 0.0136000
0.0500000 0.0180000
0.0750000 0.0210000
0.1000000 0.0234000
0.1500000 0.0267000
0.2000000 0.0288000
0.3000000 0.0308000
0.4000000 0.0305000
0.5000000 0.0285000
0.6000000 0.0253000
0.7000000 0.0208000
0.8000000 0.0154000
0.9000000 0.0091000
0.9500000 0.0057000
1.0000000 0.0020000
0.0000000 0.0000000
0.0125000 -.0103000
0.0250000 -.0136000
0.0500000 -.0180000
0.0750000 -.0210000
0.1000000 -.0234000
0.1500000 -.0267000
0.2000000 -.0288000
0.3000000 -.0308000
0.4000000 -.0305000
0.5000000 -.0285000
0.6000000 -.0253000
0.7000000 -.0208000
0.8000000 -.0154000
0.9000000 -.0091000
0.9500000 -.0057000
1.0000000 -.0020000
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Polars for NACA-M1 AIRFOIL (m1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m1-il | 50,000 | 9 | 18.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 50,000 | 5 | 20.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 100,000 | 9 | 27.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 100,000 | 5 | 24.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 200,000 | 9 | 32.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 200,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 500,000 | 9 | 38.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 500,000 | 5 | 50.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 1,000,000 | 9 | 56 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 1,000,000 | 5 | 63.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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