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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(sc20610-il) NASA SC(2)-0610 AIRFOIL | NASA SC(2)-0610 airfoil (NASA TP-2969) Max thickness 10% at 38% chord Max camber 1.8% at 82% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc20610-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20610-il | 50,000 | 9 | 23.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20610-il | 50,000 | 5 | 24.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20610-il | 100,000 | 9 | 31.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20610-il | 100,000 | 5 | 31.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20610-il | 200,000 | 9 | 41.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20610-il | 200,000 | 5 | 43.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20610-il | 500,000 | 9 | 64.9 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20610-il | 500,000 | 5 | 62.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20610-il | 1,000,000 | 9 | 74.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20610-il | 1,000,000 | 5 | 77.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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