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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(s2046-il) S2046 | Selig S2046 low Reynolds number airfoil Max thickness 9% at 26.2% chord Max camber 2.6% at 55.1% chord | Remove Airfoil details Airfoil plotter |
(dae11-il) DAE-11 AIRFOIL | Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord Max camber 6.6% at 44.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s2046-il,dae11-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2046-il | 50,000 | 9 | 38.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 50,000 | 5 | 40.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 100,000 | 9 | 58 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 100,000 | 5 | 55.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 200,000 | 9 | 77.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 200,000 | 5 | 70.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 500,000 | 9 | 101.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 500,000 | 5 | 84.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 1,000,000 | 9 | 108.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 1,000,000 | 5 | 93.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 50,000 | 9 | 6.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 50,000 | 5 | 13.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 9 | 31.3 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 5 | 32.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 9 | 79 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 5 | 83.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 9 | 135.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 5 | 132.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 9 | 177.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 5 | 165 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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