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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(ah83159-il) AH 83-159 | Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(e224-il) E224 (10.17%) | Eppler E224 low Reynolds number airfoil Max thickness 10.2% at 29.8% chord Max camber 1.5% at 54.2% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (ah83159-il,e224-il,e548-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah83159-il | 50,000 | 9 | 17.1 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 50,000 | 5 | 15.5 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 100,000 | 9 | 31.4 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 100,000 | 5 | 29 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 200,000 | 9 | 64.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 200,000 | 5 | 63.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 500,000 | 9 | 106.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 500,000 | 5 | 105.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 1,000,000 | 9 | 136.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 1,000,000 | 5 | 133.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 50,000 | 9 | 33.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 50,000 | 5 | 35.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 100,000 | 9 | 51.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 100,000 | 5 | 50.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 200,000 | 9 | 68.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 200,000 | 5 | 63.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 500,000 | 9 | 89.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 500,000 | 5 | 79.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 1,000,000 | 9 | 102.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 1,000,000 | 5 | 88.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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