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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(e548-il) EPPLER 548 AIRFOIL | Eppler E548 general aviation airfoil Max thickness 17.4% at 35.4% chord Max camber 2.2% at 26.1% chord | Remove Airfoil details Airfoil plotter |
(e552-il) EPPLER 552 AIRFOIL | Eppler E552 general aviation airfoil Max thickness 18.4% at 32.4% chord Max camber 2.6% at 51.8% chord | Remove Airfoil details Airfoil plotter |
(e554-il) EPPLER 554 AIRFOIL | Eppler E554 general aviation airfoil Max thickness 18.2% at 31.8% chord Max camber 2.7% at 56.6% chord | Remove Airfoil details Airfoil plotter |
(e64-il) E64 (8.45%) | Eppler E64 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.9% at 56.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e548-il,e552-il,e554-il,e64-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e548-il | 50,000 | 9 | 13.1 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 50,000 | 5 | 10.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 100,000 | 9 | 34.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 100,000 | 5 | 38.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 200,000 | 9 | 61.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 200,000 | 5 | 63.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 500,000 | 9 | 93.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 500,000 | 5 | 90.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 1,000,000 | 9 | 117.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 1,000,000 | 5 | 108.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 50,000 | 9 | 11 at α=-3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 50,000 | 5 | 13.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 100,000 | 9 | 31.2 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 100,000 | 5 | 43.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 200,000 | 9 | 70.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 200,000 | 5 | 70.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 500,000 | 9 | 106.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 500,000 | 5 | 100.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 1,000,000 | 9 | 131 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 1,000,000 | 5 | 119.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 50,000 | 9 | 4.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 50,000 | 5 | 18.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 100,000 | 9 | 36.4 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 100,000 | 5 | 46.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 200,000 | 9 | 69 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 200,000 | 5 | 70.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 500,000 | 9 | 103.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 500,000 | 5 | 98.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 9 | 127.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 5 | 118.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 50,000 | 9 | 41.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 100,000 | 9 | 64 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 100,000 | 5 | 62.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 200,000 | 9 | 88.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 200,000 | 5 | 81.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 500,000 | 9 | 120.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 500,000 | 5 | 103.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 1,000,000 | 9 | 140.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 1,000,000 | 5 | 113.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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