NACA M22 AIRFOIL (m22-il)
NACA M22 AIRFOIL - NACA/Munk M-22 airfoil
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(m22-il) NACA M22 AIRFOIL NACA/Munk M-22 airfoil Max thickness 6.3% at 30% chord. Max camber 6.3% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M22 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125500 0.0138600
0.0250800 0.0225200
0.0501200 0.0371300
0.0751600 0.0485500
0.1002000 0.0590600
0.1502500 0.0745000
0.2002900 0.0852300
0.3003200 0.0942900
0.4003000 0.0908600
0.5002600 0.0786200
0.6002100 0.0613900
0.7001400 0.0418500
0.8000801 0.0237200
0.9000300 0.0094800
0.9500200 0.0049200
1.0000000 0.0026500
0.0000000 0.0000000
0.0124800 -.0070400
0.0249800 -.0050800
0.0500000 0.0005300
0.0750200 0.0063500
0.1000400 0.0116600
0.1500700 0.0207000
0.2000900 0.0269300
0.3001100 0.0317900
0.4001000 0.0287600
0.5000700 0.0199200
0.6000300 0.0092900
0.7000000 -.0011400
0.7999700 -.0082800
0.8999700 -.0096100
0.9499800 -.0070800
1.0000000 -.0026500
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Polars for NACA M22 AIRFOIL (m22-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m22-il | 50,000 | 9 | 18.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 50,000 | 5 | 32.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 100,000 | 9 | 54.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 100,000 | 5 | 55.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 200,000 | 9 | 74.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 200,000 | 5 | 73.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 500,000 | 9 | 100.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 500,000 | 5 | 81.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m22-il | 1,000,000 | 9 | 115 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m22-il | 1,000,000 | 5 | 91 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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