NACA M17 AIRFOIL (m17-il)
NACA M17 AIRFOIL - NACA/Munk M-17 airfoil
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(m17-il) NACA M17 AIRFOIL NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord. Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M17 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125300 0.0155700
0.0250500 0.0234500
0.0500700 0.0358000
0.0750900 0.0456500
0.1001100 0.0535900
0.1501300 0.0650900
0.2001500 0.0731900
0.3001700 0.0814800
0.4001600 0.0798800
0.5001500 0.0710700
0.6001200 0.0576700
0.7000901 0.0424600
0.8000600 0.0268600
0.9000300 0.0129500
0.9500100 0.0070500
1.0000000 0.0020500
0.0000000 0.0000000
0.0124800 -.0104300
0.0249800 -.0115500
0.0499800 -.0110000
0.0749800 -.0094500
0.0999800 -.0075000
0.1499900 -.0041100
0.2000000 -.0014100
0.3000000 0.0007800
0.4000000 -.0009200
0.4999900 -.0046200
0.5999800 -.0096300
0.6999700 -.0123300
0.7999700 -.0130400
0.8999800 -.0101400
0.9499900 -.0067500
1.0000000 -.0020500
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Polars for NACA M17 AIRFOIL (m17-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m17-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 100,000 | 9 | 55.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 100,000 | 5 | 55.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 200,000 | 9 | 75.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 200,000 | 5 | 74.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 500,000 | 9 | 102.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 500,000 | 5 | 98.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 9 | 122.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 5 | 114.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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