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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(rae2822-il) RAE 2822 AIRFOIL | RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae2822-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae2822-il | 50,000 | 9 | 25.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 50,000 | 5 | 27 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 100,000 | 9 | 37.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 100,000 | 5 | 37.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 200,000 | 9 | 53.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 200,000 | 5 | 49.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 500,000 | 9 | 70.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 500,000 | 5 | 57.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 1,000,000 | 9 | 79 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 1,000,000 | 5 | 69.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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