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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(s3024-il) AIRFOIL 3024 9.84% | Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord Max camber 3% at 44.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s3024-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3024-il | 50,000 | 9 | 34.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 50,000 | 5 | 38.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 100,000 | 9 | 57.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 100,000 | 5 | 57.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 200,000 | 9 | 80.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 200,000 | 5 | 76.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 500,000 | 9 | 110.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 500,000 | 5 | 96.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 1,000,000 | 9 | 129 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 1,000,000 | 5 | 110.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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