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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(rae5213-il) RAE(NPL) 5213 AIRFOIL | RAE(NPL) 5213 transonic airfoil Max thickness 10% at 35.5% chord Max camber 1.4% at 69.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae5213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae5213-il | 50,000 | 9 | 29.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5213-il | 50,000 | 5 | 29.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5213-il | 100,000 | 9 | 42.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5213-il | 100,000 | 5 | 35.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5213-il | 200,000 | 9 | 49.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5213-il | 200,000 | 5 | 48.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5213-il | 500,000 | 9 | 65.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5213-il | 500,000 | 5 | 68.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5213-il | 1,000,000 | 9 | 83.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5213-il | 1,000,000 | 5 | 80.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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