Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(s3014-il) S3014-095-85 | Selig S3014 low Reynolds number airfoil Max thickness 9.5% at 29.4% chord Max camber 2.6% at 38.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s3014-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3014-il | 50,000 | 9 | 32.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3014-il | 50,000 | 5 | 36.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3014-il | 100,000 | 9 | 51.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3014-il | 100,000 | 5 | 51.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3014-il | 200,000 | 9 | 70.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3014-il | 200,000 | 5 | 65.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3014-il | 500,000 | 9 | 92.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3014-il | 500,000 | 5 | 82.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3014-il | 1,000,000 | 9 | 106.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3014-il | 1,000,000 | 5 | 96.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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