NACA M4 AIRFOIL (m4-il)
NACA M4 AIRFOIL - NACA/Munk M-4 airfoil
| Details | Dat file | Parser | |
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(m4-il) NACA M4 AIRFOIL NACA/Munk M-4 airfoil Max thickness 6.3% at 30% chord. Max camber 2.2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M4 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125900 0.0121100
0.0251300 0.0174100
0.0501900 0.0253300
0.0752400 0.0315400
0.1002700 0.0365500
0.1503300 0.0439800
0.2003700 0.0491100
0.3004000 0.0534600
0.4003800 0.0516200
0.5003400 0.0457700
0.6002800 0.0369300
0.7002000 0.0267800
0.8001300 0.0169400
0.9000599 0.0081900
0.9500400 0.0048200
1.0000000 0.0024500
0.0000000 0.0000000
0.0124300 -.0089900
0.0249200 -.0105900
0.0499200 -.0112700
0.0749200 -.0113600
0.0999200 -.0110400
0.1499200 -.0101200
0.1999300 -.0091900
0.2999300 -.0093300
0.3999200 -.0106800
0.4999000 -.0129200
0.5998900 -.0149700
0.6998800 -.0161100
0.7998900 -.0148600
0.8999200 -.0106000
0.9499500 -.0071800
1.0000000 -.0024500
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Polars for NACA M4 AIRFOIL (m4-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m4-il | 50,000 | 9 | 33.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 50,000 | 5 | 34 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 100,000 | 9 | 45.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 100,000 | 5 | 44.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 200,000 | 9 | 57.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 200,000 | 5 | 55.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 500,000 | 9 | 71.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 500,000 | 5 | 66.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 1,000,000 | 9 | 80.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 1,000,000 | 5 | 73.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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