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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(clarkv-il) CLARK V AIRFOIL | CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(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 |
(ames03-il) NASA/AMES A-03 AIRFOIL | NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarkv-il,amsoil2-il,ames03-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarkv-il | 50,000 | 9 | 35.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 50,000 | 5 | 36.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 100,000 | 9 | 57.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 100,000 | 5 | 56.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 200,000 | 9 | 80.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 200,000 | 5 | 75.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 500,000 | 9 | 110.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 500,000 | 5 | 95.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 1,000,000 | 9 | 129.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 1,000,000 | 5 | 105.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| ames03-il | 50,000 | 9 | 27.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 50,000 | 5 | 27.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 100,000 | 9 | 34.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 100,000 | 5 | 39.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 200,000 | 9 | 50.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 200,000 | 5 | 53.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 500,000 | 9 | 72.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 500,000 | 5 | 70.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 1,000,000 | 9 | 87.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 1,000,000 | 5 | 83.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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