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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(e343-il) EPPLER 343 AIRFOIL | Eppler E343 flying wing airfoil Max thickness 14.5% at 30.9% chord Max camber 4% at 26% chord | Remove Airfoil details Airfoil plotter |
(clarkys-il) CLARK YS AIRFOIL | CLARK YS airfoil Max thickness 11.7% at 30% chord Max camber 2.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(usa5-il) USA 5 AIRFOIL | USA-5 airfoil Max thickness 6.4% at 30% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e343-il,clarkys-il,usa5-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e343-il | 50,000 | 9 | 14.5 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 50,000 | 5 | 24.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 100,000 | 9 | 30.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 100,000 | 5 | 43.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 200,000 | 9 | 58.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 200,000 | 5 | 64.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 500,000 | 9 | 92.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 500,000 | 5 | 87.9 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 1,000,000 | 9 | 114.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 1,000,000 | 5 | 113.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 50,000 | 9 | 23.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 50,000 | 5 | 31.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 100,000 | 9 | 45.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 100,000 | 5 | 47 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 200,000 | 9 | 62.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 200,000 | 5 | 58.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 500,000 | 9 | 76.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 500,000 | 5 | 68.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 1,000,000 | 9 | 85.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 1,000,000 | 5 | 80.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 50,000 | 9 | 38.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 50,000 | 5 | 40.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 100,000 | 9 | 55.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 100,000 | 5 | 56.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 200,000 | 9 | 72.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 200,000 | 5 | 71 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 500,000 | 9 | 95 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 500,000 | 5 | 91.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 1,000,000 | 9 | 112.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 1,000,000 | 5 | 99.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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