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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(s3025-il) S3025 9.38% | Selig S3025 low Reynolds number airfoil Max thickness 9.4% at 30.9% chord Max camber 3% at 44.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s3025-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3025-il | 50,000 | 9 | 33.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 50,000 | 5 | 39.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 100,000 | 9 | 57 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 100,000 | 5 | 58.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 200,000 | 9 | 80 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 200,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 500,000 | 9 | 109.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 500,000 | 5 | 99.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 1,000,000 | 9 | 130.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 1,000,000 | 5 | 114.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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