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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(amsoil2-il) RUTAN WING AIRFOIL | Rutan AMSOIL racer wing airfoil Max thickness 11.8% at 39% chord Max camber 1% at 48% chord | Remove Airfoil details Airfoil plotter |
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Polars for (amsoil2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| amsoil2-il | 50,000 | 9 | 25.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil2-il | 50,000 | 5 | 25.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil2-il | 100,000 | 9 | 38.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil2-il | 100,000 | 5 | 35.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil2-il | 200,000 | 9 | 48.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil2-il | 200,000 | 5 | 42.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil2-il | 500,000 | 9 | 56.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil2-il | 500,000 | 5 | 61.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil2-il | 1,000,000 | 9 | 74.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil2-il | 1,000,000 | 5 | 77.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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