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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(e546-il) EPPLER 546 AIRFOIL | Eppler E546 general aviation airfoil Max thickness 16.2% at 40.3% chord Max camber 1.8% at 26.2% 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 |
(e360-il) EPPLER 360 AIRFOIL | Eppler E360 rotorcraft airfoil Max thickness 12.2% at 36.9% chord Max camber 1.6% at 27.2% chord | Remove Airfoil details Airfoil plotter |
(e549-il) EPPLER 549 AIRFOIL | Eppler E549 general aviation airfoil Max thickness 18.1% at 38.7% chord Max camber 2% at 34% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e546-il,e551-il,e547-il,e360-il,e549-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e546-il | 50,000 | 9 | 8.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 50,000 | 5 | 21.6 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 100,000 | 9 | 44.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 100,000 | 5 | 43.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 200,000 | 9 | 61.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 200,000 | 5 | 61.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 500,000 | 9 | 87.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 500,000 | 5 | 82.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 1,000,000 | 9 | 106.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 1,000,000 | 5 | 96.6 at α=5.5° | 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 | |
| e360-il | 50,000 | 9 | 30.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 50,000 | 5 | 31.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 100,000 | 9 | 47.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 100,000 | 5 | 46 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 200,000 | 9 | 63.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 200,000 | 5 | 52.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 500,000 | 9 | 69.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 500,000 | 5 | 69 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 1,000,000 | 9 | 86 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 1,000,000 | 5 | 84 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e549-il | 50,000 | 9 | 4.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e549-il | 50,000 | 5 | 14.7 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e549-il | 100,000 | 9 | 43.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e549-il | 100,000 | 5 | 44.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e549-il | 200,000 | 9 | 66.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e549-il | 200,000 | 5 | 66.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e549-il | 500,000 | 9 | 96 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e549-il | 500,000 | 5 | 90.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e549-il | 1,000,000 | 9 | 117.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e549-il | 1,000,000 | 5 | 106 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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