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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(amsoil1-il) RUTAN CANARD AIRFOIL | Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord | Remove Airfoil details Airfoil plotter |
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Polars for (amsoil1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| amsoil1-il | 50,000 | 9 | 33 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 50,000 | 5 | 31.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 9 | 48.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 5 | 46.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 9 | 67.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 5 | 59.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 9 | 86.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 5 | 68.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 9 | 93 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 5 | 81.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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