NACA M19 AIRFOIL (m19-il)
NACA M19 AIRFOIL - NACA/Munk M-19 airfoil
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(m19-il) NACA M19 AIRFOIL NACA/Munk M-19 airfoil Max thickness 6.2% at 30% chord. Max camber 6% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M19 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124700 0.0129300
0.0249500 0.0213600
0.0499200 0.0356100
0.0748900 0.0465700
0.0998700 0.0566300
0.1498400 0.0709400
0.1998100 0.0817600
0.2997900 0.0911900
0.3998000 0.0888200
0.4998200 0.0786500
0.5998500 0.0632800
0.6998900 0.0457100
0.7999400 0.0280400
0.8999700 0.0132700
0.9499800 0.0070800
1.0000000 0.0019000
0.0000000 0.0000000
0.0125200 -.0071700
0.0250100 -.0054400
0.0500000 -.0005800
0.0749900 0.0047700
0.0999800 0.0098300
0.1499600 0.0182400
0.1999400 0.0241600
0.2999300 0.0294900
0.3999400 0.0277200
0.4999500 0.0210500
0.5999700 0.0122800
0.6999900 0.0037100
0.8000100 -.0026600
0.9000100 -.0052300
0.9500100 -.0043100
1.0000000 -.0019000
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Polars for NACA M19 AIRFOIL (m19-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m19-il | 50,000 | 9 | 20.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 50,000 | 5 | 37.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 100,000 | 9 | 57.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 100,000 | 5 | 57.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 200,000 | 9 | 77.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 200,000 | 5 | 75.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 500,000 | 9 | 102.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 500,000 | 5 | 83 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 9 | 117.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 5 | 92.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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