NACA M5 AIRFOIL (m5-il)
NACA M5 AIRFOIL - NACA/Munk M-5 airfoil
| Details | Dat file | Parser | |
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(m5-il) NACA M5 AIRFOIL NACA/Munk M-5 airfoil Max thickness 8.2% at 30.1% chord. Max camber 2.1% at 30.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M5 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0126300 0.0137800
0.0251900 0.0201700
0.0502700 0.0293300
0.0753400 0.0367000
0.1003900 0.0424700
0.1504700 0.0511100
0.2005300 0.0569500
0.3005700 0.0617200
0.4005600 0.0599900
0.5004900 0.0533700
0.6004000 0.0435500
0.7003000 0.0323200
0.8001900 0.0210000
0.9001000 0.0105700
0.9500600 0.0061100
1.0000000 0.0031500
0.0000000 0.0000000
0.0123800 -.0125100
0.0248500 -.0161300
0.0498300 -.0184600
0.0748200 -.0193900
0.0998200 -.0198200
0.1498200 -.0198900
0.1998100 -.0200500
0.2998100 -.0203700
0.3998000 -.0219000
0.4997800 -.0233200
0.5997800 -.0242500
0.6997800 -.0236700
0.7998101 -.0204000
0.8998700 -.0139200
0.9499199 -.0087900
1.0000000 -.0031500
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Polars for NACA M5 AIRFOIL (m5-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m5-il | 50,000 | 9 | 32.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 50,000 | 5 | 34 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 100,000 | 9 | 47.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 100,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 200,000 | 9 | 60.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 200,000 | 5 | 57.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 500,000 | 9 | 76.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 500,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 9 | 86.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 5 | 76.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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