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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(sc20612-il) NASA SC(2)-0612 AIRFOIL | NASA SC(2)-0612 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.9% at 81% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc20612-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20612-il | 50,000 | 9 | 24.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 50,000 | 5 | 23.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 100,000 | 9 | 29.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 100,000 | 5 | 31.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 200,000 | 9 | 40.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 200,000 | 5 | 44.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 500,000 | 9 | 63.6 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 500,000 | 5 | 65 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 1,000,000 | 9 | 77.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 1,000,000 | 5 | 79.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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