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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(e1230-il) EPPLER 1230 AIRFOIL | Eppler E1230 general aviation airfoil (Long-EZ and Defiant wing airfoil) Max thickness 17.4% at 30.9% chord Max camber 3.6% at 25.6% chord | Remove Airfoil details Airfoil plotter |
(e168-il) E168 (12.45%) | Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e1233-il) EPPLER 1233 AIRFOIL | Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord Max camber 4.4% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e1230-il,e168-il,e1233-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1230-il | 50,000 | 9 | 16.7 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 50,000 | 5 | 24.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 9 | 35.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 9 | 56.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 5 | 60.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 9 | 85.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 5 | 86.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 9 | 111.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 5 | 104.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 50,000 | 9 | 22.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 50,000 | 5 | 28 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 100,000 | 9 | 38.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 100,000 | 5 | 40.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 200,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 200,000 | 5 | 52.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 500,000 | 5 | 67.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 9 | 87 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 5 | 77.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 9 | 15.7 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 5 | 21.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 9 | 34 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 5 | 41.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 9 | 56.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 5 | 58.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 9 | 81 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 5 | 81.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 9 | 104.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 5 | 103.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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