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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(sc20010-il) NASA SC(2)-0010 AIRFOIL | NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc20010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20010-il | 50,000 | 9 | 23.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 5 | 22.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 5 | 28.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 9 | 39.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 5 | 39 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 9 | 52 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 5 | 56.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 9 | 67.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 5 | 70.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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