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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(sc20503-il) NASA SC(2)-0503 AIRFOIL | NASA SC(2)-0503 airfoil (NASA TP-2969) Max thickness 3% at 32% chord Max camber 0.8% at 82% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc20503-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20503-il | 50,000 | 9 | 19.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 50,000 | 5 | 19.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 100,000 | 9 | 26.5 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 100,000 | 5 | 24 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 200,000 | 9 | 52.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 200,000 | 5 | 32.1 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 500,000 | 9 | 50.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 500,000 | 5 | 35.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20503-il | 1,000,000 | 9 | 71.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20503-il | 1,000,000 | 5 | 42.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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