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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(e59-il) EPPLER 59 AIRFOIL | Eppler E59 low Reynolds number airfoil Max thickness 5.6% at 25% chord Max camber 5.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(hs1708-il) HAM-STD HS1-708 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 7.9% at 22% chord Max camber 5% at 46% chord | Remove Airfoil details Airfoil plotter |
(e853-il) EPPLER E853 AIRFOIL | Eppler E853 propeller airfoil Max thickness 11.6% at 37.1% chord Max camber 3.1% at 56.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e59-il,hs1708-il,e853-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e59-il | 50,000 | 9 | 43.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 50,000 | 5 | 46.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 100,000 | 9 | 69.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 100,000 | 5 | 70.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 200,000 | 9 | 103.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 200,000 | 5 | 99.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 500,000 | 9 | 155.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 500,000 | 5 | 119.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 1,000,000 | 9 | 188.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 1,000,000 | 5 | 108.8 at α=-1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 50,000 | 9 | 42.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 50,000 | 5 | 43 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 100,000 | 9 | 67.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 100,000 | 5 | 66.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 200,000 | 9 | 97.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 200,000 | 5 | 92.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 500,000 | 9 | 139.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 500,000 | 5 | 120.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 1,000,000 | 9 | 169 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 1,000,000 | 5 | 117 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 50,000 | 9 | 35.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 50,000 | 5 | 35.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 100,000 | 9 | 60.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 100,000 | 5 | 59.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 200,000 | 9 | 85.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 200,000 | 5 | 82.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 500,000 | 9 | 120.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 500,000 | 5 | 103 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 1,000,000 | 9 | 135.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 1,000,000 | 5 | 114.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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