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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(e585-il) EPPLER 585 AIRFOIL | Eppler E585 sailplane airfoil Max thickness 14.6% at 37.6% chord Max camber 4.2% at 42.8% chord | Remove Airfoil details Airfoil plotter |
(hs1404-il) HAM-STD HS1-404 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 4% at 18% chord Max camber 3.1% at 46% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e585-il,hs1404-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e585-il | 50,000 | 9 | 8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 50,000 | 5 | 21.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 100,000 | 5 | 47.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 200,000 | 9 | 81.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 200,000 | 5 | 78.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 500,000 | 9 | 118 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 500,000 | 5 | 110.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 9 | 146.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 5 | 131.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 50,000 | 9 | 42.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 50,000 | 5 | 42.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 100,000 | 5 | 59.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 200,000 | 9 | 84.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 200,000 | 5 | 78.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 500,000 | 9 | 114.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 500,000 | 5 | 102.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 1,000,000 | 9 | 134.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 1,000,000 | 5 | 113.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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