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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(c5a-il) LOCKHEED C-5A BL0 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% 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 |
(ames02-il) NASA/AMES A-02 AIRFOIL | NASA/AMES/Hicks A-02 transonic rotorcraft airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (c5a-il,amsoil2-il,ames02-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c5a-il | 50,000 | 9 | 27.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 5 | 32.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 9 | 44.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 5 | 40.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 9 | 56.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 5 | 55.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 9 | 68.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 5 | 72.3 at α=9.75° | 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 | |
| ames02-il | 50,000 | 9 | 24.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 50,000 | 5 | 22.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 100,000 | 9 | 31.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 100,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 200,000 | 9 | 37.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 200,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 500,000 | 9 | 54.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 500,000 | 5 | 58.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 1,000,000 | 9 | 69.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 1,000,000 | 5 | 72.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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