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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(fx05191-il) WORTMANN FX 05-191 AIRFOIL | Wortmann FX 05-191 airfoil Max thickness 19.1% at 37.1% chord Max camber 2.6% at 50% chord | Remove Airfoil details Airfoil plotter |
(eiffel385-il) Eiffel 385 (S.T. Ae) | Eiffel 385 (S.T. Ae) airfoil Max thickness 13.4% at 20% chord Max camber 4.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(e864-il) EPPLER 864 STRUT AIRFOIL | Eppler E864 strut airfoil Max thickness 38.8% at 32.7% chord Max camber 0.1% at 10.8% chord | Remove Airfoil details Airfoil plotter |
(fg4-il) Fage & Collins 4 | Fage & Collins 4 airfoil Max thickness 12.7% at 30% chord Max camber 4.7% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx05191-il,eiffel385-il,e864-il,fg4-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx05191-il | 50,000 | 9 | 18.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 50,000 | 5 | 14 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 100,000 | 9 | 27.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 100,000 | 5 | 29.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 200,000 | 9 | 55.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 200,000 | 5 | 57.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 500,000 | 9 | 89.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 500,000 | 5 | 89.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 1,000,000 | 9 | 118.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 1,000,000 | 5 | 112.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel385-il | 50,000 | 9 | 25.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel385-il | 50,000 | 5 | 32.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel385-il | 100,000 | 9 | 52.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel385-il | 100,000 | 5 | 55.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel385-il | 200,000 | 9 | 76 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel385-il | 200,000 | 5 | 74.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel385-il | 500,000 | 9 | 106.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel385-il | 500,000 | 5 | 93.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel385-il | 1,000,000 | 9 | 123.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel385-il | 1,000,000 | 5 | 97.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 50,000 | 9 | 2.5 at α=-8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 50,000 | 5 | 3.7 at α=-2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 100,000 | 9 | 4.2 at α=-4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 100,000 | 5 | 4.9 at α=-3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 200,000 | 9 | 7.6 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 200,000 | 5 | 15 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 500,000 | 9 | 37.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 500,000 | 5 | 33.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e864-il | 1,000,000 | 9 | 50.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e864-il | 1,000,000 | 5 | 46.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 50,000 | 9 | 30.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 50,000 | 5 | 32.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 100,000 | 9 | 51.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 100,000 | 5 | 47.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 200,000 | 9 | 65.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 200,000 | 5 | 47 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 500,000 | 9 | 62.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 500,000 | 5 | 58.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 1,000,000 | 9 | 71.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 1,000,000 | 5 | 72.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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