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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(s4110-il) S4110 | Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord Max camber 3.1% at 45.4% chord | Remove Airfoil details Airfoil plotter |
(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 |
(sc21006-il) NASA SC(2)-1006 AIRFOIL | NASA SC(2)-1006 airfoil Max thickness 6% at 30% chord Max camber 2.6% at 73% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4110-il,s3025-il,sc21006-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4110-il | 50,000 | 9 | 39.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 50,000 | 5 | 40.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 100,000 | 9 | 60.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 100,000 | 5 | 57.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 200,000 | 9 | 81.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 200,000 | 5 | 73.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 500,000 | 9 | 107.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 500,000 | 5 | 89.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 1,000,000 | 9 | 122.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 1,000,000 | 5 | 99.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| sc21006-il | 50,000 | 9 | 28.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 50,000 | 5 | 29.8 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 100,000 | 9 | 39.2 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 100,000 | 5 | 48.9 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 200,000 | 9 | 66.5 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 200,000 | 5 | 61.3 at α=-1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 500,000 | 9 | 101.9 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 500,000 | 5 | 92 at α=-2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21006-il | 1,000,000 | 9 | 130.4 at α=-2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21006-il | 1,000,000 | 5 | 100.2 at α=-3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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