NACA M13 AIRFOIL (m13-il)
NACA M13 AIRFOIL - NACA/Munk M-13 airfoil
| Details | Dat file | Parser | |
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(m13-il) NACA M13 AIRFOIL NACA/Munk M-13 airfoil Max thickness 6.2% at 30% chord. Max camber 3.8% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M13 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0127800
0.0250000 0.0193700
0.0500000 0.0296400
0.0750000 0.0379100
0.1000000 0.0446800
0.1500000 0.0554200
0.2000000 0.0627600
0.3000000 0.0701400
0.4000000 0.0694200
0.5000000 0.0636000
0.6000000 0.0537800
0.7000000 0.0418600
0.8000000 0.0292400
0.9000000 0.0164200
0.9500000 0.0105600
1.0000000 0.0044000
0.0000000 0.0000000
0.0125000 -.0081200
0.0250000 -.0081300
0.0500000 -.0079100
0.0750000 -.0043900
0.1000000 -.0022200
0.1500000 0.0019200
0.2000000 0.0050600
0.3000000 0.0080400
0.4000000 0.0077200
0.5000000 0.0055000
0.6000000 0.0022800
0.7000000 -.0006400
0.8000000 -.0022600
0.9000000 -.0022800
0.9500000 -.0014400
1.0000000 0.0000000
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Polars for NACA M13 AIRFOIL (m13-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m13-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 50,000 | 5 | 40.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 100,000 | 9 | 56.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 100,000 | 5 | 56.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 200,000 | 9 | 74.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 200,000 | 5 | 73.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 500,000 | 9 | 98.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 500,000 | 5 | 95 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 1,000,000 | 9 | 115.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 1,000,000 | 5 | 86.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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