NACA M16 AIRFOIL (m16-il)
NACA M16 AIRFOIL - NACA/Munk M-16 airfoil
| Details | Dat file | Parser | |
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(m16-il) NACA M16 AIRFOIL NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord. Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M16 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125100 0.0120900
0.0250100 0.0187900
0.0500100 0.0297700
0.0750200 0.0385600
0.1000200 0.0458500
0.1500300 0.0572200
0.2000300 0.0650000
0.3000400 0.0718500
0.4000400 0.0700000
0.5000300 0.0620500
0.6000200 0.0497000
0.7000200 0.0361500
0.8000100 0.0227000
0.9000100 0.0108500
0.9500000 0.0061200
1.0000000 0.0028000
0.0000000 0.0000000
0.0125000 -.0081100
0.0250000 -.0082100
0.0500000 -.0058200
0.0750000 -.0032400
0.1000000 -.0005500
0.1500000 0.0040200
0.2000000 0.0075000
0.3000100 0.0103500
0.4000000 0.0086000
0.5000000 0.0044500
0.6000000 -.0014000
0.7000000 -.0060500
0.8000000 -.0086000
0.9000000 -.0074500
0.9500000 -.0052700
1.0000000 -.0028000
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Polars for NACA M16 AIRFOIL (m16-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m16-il | 50,000 | 9 | 39 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 50,000 | 5 | 38.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 100,000 | 9 | 53.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 100,000 | 5 | 53.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 200,000 | 5 | 68.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 500,000 | 9 | 92.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 500,000 | 5 | 88.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 9 | 109.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 5 | 102.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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