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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(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) | NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nasasc2-0714-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nasasc2-0714-il | 50,000 | 9 | 24.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 50,000 | 5 | 22.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 9 | 28.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 5 | 31.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 9 | 36.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 5 | 43.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 9 | 66 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 5 | 64 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 9 | 83.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 5 | 80 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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