NACA M9 AIRFOIL (m9-il)
NACA M9 AIRFOIL - NACA/Munk M-9 airfoil
| Details | Dat file | Parser | |
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(m9-il) NACA M9 AIRFOIL NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord. Max camber 7.2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M9 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0312000
0.0250000 0.0459000
0.0500000 0.0639000
0.0750000 0.0779000
0.1000000 0.0885000
0.1500000 0.1011000
0.2000000 0.1075000
0.2500000 0.1111000
0.3000000 0.1110000
0.4000000 0.1024000
0.5000000 0.0878000
0.6000000 0.0695000
0.7000000 0.0484000
0.8000000 0.0294000
0.9000000 0.0122000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0083000
0.0250000 -.0112000
0.0500000 -.0122000
0.0750000 -.0107000
0.1000000 -.0079000
0.1500000 -.0029000
0.2000000 0.0053000
0.2500000 0.0226000
0.3000000 0.0326000
0.4000000 0.0391000
0.5000000 0.0346000
0.6000000 0.0278000
0.7000000 0.0172000
0.8000000 0.0073000
0.9000000 0.0000000
1.0000000 0.0000000
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Polars for NACA M9 AIRFOIL (m9-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m9-il | 50,000 | 9 | 15.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 50,000 | 5 | 30.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 100,000 | 9 | 43.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 100,000 | 5 | 49.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 200,000 | 9 | 63.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 200,000 | 5 | 63.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 500,000 | 9 | 80.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 500,000 | 5 | 81.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 1,000,000 | 9 | 99.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 1,000,000 | 5 | 99.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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