NACA M10 AIRFOIL (m10-il)
NACA M10 AIRFOIL - NACA/Munk M-10 airfoil
| Details | Dat file | Parser | |
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(m10-il) NACA M10 AIRFOIL NACA/Munk M-10 airfoil Max thickness 6.2% at 30% chord. Max camber 1.9% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M10 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124900 0.0115100
0.0249800 0.0163300
0.0499700 0.0234600
0.0749700 0.0290900
0.0999600 0.0338100
0.1499500 0.0407700
0.1999500 0.0455300
0.2999400 0.0500400
0.3999400 0.0495600
0.4999500 0.0453700
0.5999600 0.0385900
0.6999700 0.0302000
0.7999800 0.0210200
0.8999900 0.0116300
0.9499900 0.0068900
1.0000000 0.0019500
0.0000000 0.0000000
0.0125100 -.0092900
0.0250100 -.0114700
0.0500100 -.0129400
0.0750200 -.0132100
0.1000200 -.0131800
0.1500100 -.0128300
0.2000100 -.0123700
0.3000100 -.0118500
0.4000100 -.0120400
0.5000100 -.0125200
0.6000100 -.0126100
0.7000100 -.0116900
0.8000100 -.0097800
0.9000100 -.0065600
0.9500100 -.0044100
1.0000000 -.0019500
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Polars for NACA M10 AIRFOIL (m10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m10-il | 50,000 | 9 | 34.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 50,000 | 5 | 34.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 100,000 | 9 | 46.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 100,000 | 5 | 45.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 200,000 | 9 | 58.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 200,000 | 5 | 54.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 500,000 | 9 | 72.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 500,000 | 5 | 64.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 1,000,000 | 9 | 80.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 1,000,000 | 5 | 75.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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