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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(rcsc2-il) NASA/LANGLEY RC-SC2 AIRFOIL | NASA/Langley RC-SC2 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 0.5% at 62.5% chord | Remove Airfoil details Airfoil plotter |
(e435-il) EPPLER 435 AIRFOIL | Eppler E435 sailplane airfoil Max thickness 16.2% at 40.9% chord Max camber 4.4% at 56.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rcsc2-il,e435-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rcsc2-il | 50,000 | 9 | 24.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 50,000 | 5 | 25.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 100,000 | 9 | 37.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 100,000 | 5 | 33.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 200,000 | 9 | 49.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 200,000 | 5 | 41.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 500,000 | 9 | 54.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 500,000 | 5 | 56.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 1,000,000 | 9 | 66.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 1,000,000 | 5 | 69.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e435-il | 50,000 | 9 | 7.6 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e435-il | 50,000 | 5 | 19.4 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e435-il | 100,000 | 9 | 48 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e435-il | 100,000 | 5 | 44.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e435-il | 200,000 | 9 | 79.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e435-il | 200,000 | 5 | 78.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e435-il | 500,000 | 9 | 119.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e435-il | 500,000 | 5 | 111.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e435-il | 1,000,000 | 9 | 148.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e435-il | 1,000,000 | 5 | 133 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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