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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(e230-il) E230 (9.96%) | Eppler E230 airfoil Max thickness 10% at 29.3% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e230-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e230-il | 50,000 | 9 | 23 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 50,000 | 5 | 24.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 100,000 | 9 | 32.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 100,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 200,000 | 9 | 41.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 200,000 | 5 | 38.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 500,000 | 9 | 50.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 500,000 | 5 | 49.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 1,000,000 | 9 | 57.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 1,000,000 | 5 | 58 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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