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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(rae5215-il) RAE 5215 AIRFOIL | RAE 5215 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.5% at 69.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae5215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae5215-il | 50,000 | 9 | 28.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5215-il | 50,000 | 5 | 26.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5215-il | 100,000 | 9 | 38 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5215-il | 100,000 | 5 | 35.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5215-il | 200,000 | 9 | 43.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5215-il | 200,000 | 5 | 49.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5215-il | 500,000 | 9 | 67.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5215-il | 500,000 | 5 | 68.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5215-il | 1,000,000 | 9 | 83.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5215-il | 1,000,000 | 5 | 81.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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