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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(rae100-il) RAE 100 AIRFOIL | RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae100-il | 50,000 | 9 | 24.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 50,000 | 5 | 26.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 100,000 | 9 | 35.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 100,000 | 5 | 35.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 200,000 | 9 | 46.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 200,000 | 5 | 45 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 500,000 | 9 | 60.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 500,000 | 5 | 60.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 1,000,000 | 9 | 74.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 1,000,000 | 5 | 74.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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