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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(fx74080-il) WORTMANN FX 74-080 | Wortmann FX 74-080 airfoil Max thickness 8.2% at 43.5% chord Max camber 4.3% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(fx73170-il) WORTMANN FX 73-170 | Wortmann FX 73-170 airfoil Max thickness 17.1% at 43.5% chord Max camber 4.4% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(goe280-il) GOE 280 (DAIMLER XI) AIRFOIL | Gottingen 280 (DAIMLER XI) airfoil Max thickness 7.9% at 30% chord Max camber 4.5% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx74080-il,fx73170-il,goe280-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74080-il | 50,000 | 9 | 24.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 50,000 | 5 | 27.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 9 | 39.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 5 | 58 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 9 | 80.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 5 | 87 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 9 | 134.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 5 | 131.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 9 | 173.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 5 | 164.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 50,000 | 9 | 17.8 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 50,000 | 5 | 15.1 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 100,000 | 9 | 24.9 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 100,000 | 5 | 24.5 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 200,000 | 9 | 43.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 200,000 | 5 | 45.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 500,000 | 9 | 110.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 500,000 | 5 | 112.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170-il | 1,000,000 | 9 | 151.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170-il | 1,000,000 | 5 | 147.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 50,000 | 9 | 37.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 50,000 | 5 | 41.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 9 | 55.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 5 | 56.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 9 | 72.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 5 | 70.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 9 | 91.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 5 | 79.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 9 | 98.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 5 | 87.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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