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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(e423-il) E423 | Eppler E423 high lift airfoil Max thickness 12.5% at 23.7% chord Max camber 9.5% at 41.4% chord | Remove Airfoil details Airfoil plotter |
(e551-il) EPPLER 551 AIRFOIL | Eppler E551 general aviation airfoil Max thickness 18.2% at 32.4% chord Max camber 2.8% at 57.1% chord | Remove Airfoil details Airfoil plotter |
(e547-il) EPPLER 547 AIRFOIL | Eppler E547 general aviation airfoil Max thickness 17.4% at 40.3% chord Max camber 2% at 30.7% chord | Remove Airfoil details Airfoil plotter |
(e502-il) EPPLER 502 AIRFOIL | Eppler E502 general purpose airfoil Max thickness 15.6% at 42.1% chord Max camber 1.5% at 32.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e423-il,e551-il,e547-il,e502-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e423-il | 50,000 | 9 | 6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 50,000 | 5 | 13.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 100,000 | 9 | 12.5 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 100,000 | 5 | 51.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 200,000 | 9 | 73.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 200,000 | 5 | 84.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 500,000 | 9 | 123.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 500,000 | 5 | 120.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 1,000,000 | 9 | 156.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 1,000,000 | 5 | 145.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 50,000 | 9 | 4.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 50,000 | 5 | 14.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 100,000 | 9 | 43.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 100,000 | 5 | 47.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 200,000 | 9 | 72.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 200,000 | 5 | 70 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 500,000 | 9 | 102.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 500,000 | 5 | 95.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 1,000,000 | 9 | 125.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 1,000,000 | 5 | 113.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 50,000 | 9 | 6.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 50,000 | 5 | 15 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 100,000 | 9 | 41.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 100,000 | 5 | 41 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 200,000 | 9 | 61.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 200,000 | 5 | 62 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 500,000 | 9 | 90.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 500,000 | 5 | 85.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 1,000,000 | 9 | 111.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 1,000,000 | 5 | 101.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 50,000 | 9 | 24.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 50,000 | 5 | 21 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 100,000 | 9 | 45.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 100,000 | 5 | 36.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 200,000 | 9 | 58.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 200,000 | 5 | 58 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 500,000 | 9 | 88 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 500,000 | 5 | 80 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 1,000,000 | 9 | 106.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 1,000,000 | 5 | 90.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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