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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(rae5212-il) RAE(NPL) 5212 AIRFOIL | RAE(NPL) 5212 transonic airfoil Max thickness 11.9% at 35.5% chord Max camber 1.8% at 69.1% chord | Remove Airfoil details Airfoil plotter |
(goe513-il) GOE 513 AIRFOIL | Gottingen 513 airfoil Max thickness 16.6% at 29.8% chord Max camber 5.2% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae5212-il,goe513-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae5212-il | 50,000 | 9 | 31.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 50,000 | 5 | 30.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 100,000 | 9 | 47.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 100,000 | 5 | 40.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 200,000 | 9 | 57.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 200,000 | 5 | 48.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 500,000 | 9 | 69.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 500,000 | 5 | 63.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 1,000,000 | 9 | 76.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 1,000,000 | 5 | 80.3 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 50,000 | 9 | 10.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 50,000 | 5 | 28.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 100,000 | 9 | 44.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 200,000 | 9 | 58.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 200,000 | 5 | 54.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 500,000 | 9 | 75.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 500,000 | 5 | 66.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe513-il | 1,000,000 | 9 | 86.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe513-il | 1,000,000 | 5 | 76.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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