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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(rae103-il) RAE 103 AIRFOIL | RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae103-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae103-il | 50,000 | 9 | 27.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 50,000 | 5 | 27.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 100,000 | 9 | 40.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 100,000 | 5 | 36.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 200,000 | 9 | 48.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 200,000 | 5 | 39.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 500,000 | 9 | 54.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 500,000 | 5 | 52.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 1,000,000 | 9 | 62.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 1,000,000 | 5 | 66 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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