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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(e342-il) EPPLER 342 AIRFOIL | Eppler E342 flying wing airfoil Max thickness 14.3% at 31.8% chord Max camber 3.5% at 22.2% chord | Remove Airfoil details Airfoil plotter |
(goe417a-il) GOE 417A (GEW. PLATTE) AIRFOIL | Gottingen 417A (GEW. PLATTE) airfoil Max thickness 3.2% at 2.5% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(s4083-il) S4083 (8%) | Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e342-il,goe417a-il,s4083-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e342-il | 50,000 | 9 | 14.6 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 50,000 | 5 | 24.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 100,000 | 9 | 30.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 100,000 | 5 | 43.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 200,000 | 9 | 59.4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 200,000 | 5 | 61.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 500,000 | 9 | 88.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 500,000 | 5 | 83.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 1,000,000 | 9 | 108.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 1,000,000 | 5 | 106.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 50,000 | 9 | 46.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 50,000 | 5 | 45.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 100,000 | 9 | 65.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 100,000 | 5 | 56.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 200,000 | 9 | 71.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 200,000 | 5 | 61.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 500,000 | 9 | 75.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 500,000 | 5 | 68.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe417a-il | 1,000,000 | 9 | 86.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe417a-il | 1,000,000 | 5 | 116.9 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 9 | 31.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 5 | 38.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 9 | 51.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 9 | 73.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 9 | 102.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 5 | 98.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 9 | 124.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 5 | 115.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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