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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(e336-il) EPPLER 336 AIRFOIL | Eppler E336 flying wing airfoil Max thickness 12.8% at 28.1% chord Max camber 2.8% at 23.4% chord | Remove Airfoil details Airfoil plotter |
(raf30-il) RAF 30 AIRFOIL | RAF-30 airfoil Max thickness 12.6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e336-il,raf30-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e336-il | 50,000 | 9 | 16.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 50,000 | 5 | 25.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 100,000 | 9 | 35.7 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 100,000 | 5 | 44.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 200,000 | 9 | 61.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 200,000 | 5 | 62.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 500,000 | 9 | 87.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 500,000 | 5 | 78.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 1,000,000 | 9 | 99 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 1,000,000 | 5 | 96.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 50,000 | 9 | 28.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 50,000 | 5 | 28.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 9 | 41.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 5 | 39.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 9 | 52.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 5 | 45.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 9 | 58.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 5 | 58.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 9 | 69.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 5 | 71.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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