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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(goe449-il) GOE 449 AIRFOIL | Gottingen 449 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(e71-il) E71 (5.15%) | Eppler E71 low Reynolds number airfoil Max thickness 5.2% at 25.7% chord Max camber 4.4% at 54% chord | Remove Airfoil details Airfoil plotter |
(e636-il) EPPLER 636 AIRFOIL | Eppler E636 airfoil Max thickness 11.9% at 26.9% chord Max camber 3.2% at 22.9% 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 (goe449-il,e71-il,e636-il,hs1404-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe449-il | 50,000 | 9 | 4.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 50,000 | 5 | 12.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 100,000 | 9 | 34.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 100,000 | 5 | 43.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 200,000 | 9 | 70.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 200,000 | 5 | 65.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 500,000 | 9 | 97.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 500,000 | 5 | 87.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe449-il | 1,000,000 | 9 | 117.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe449-il | 1,000,000 | 5 | 107.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 50,000 | 9 | 48.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 50,000 | 5 | 49.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 100,000 | 9 | 75.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 100,000 | 5 | 74 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 200,000 | 9 | 108.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 200,000 | 5 | 103.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 500,000 | 9 | 162.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 500,000 | 5 | 143.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 1,000,000 | 9 | 205 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 1,000,000 | 5 | 139 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 50,000 | 9 | 14.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 50,000 | 5 | 24.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 100,000 | 9 | 33 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 100,000 | 5 | 44 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 200,000 | 9 | 61.7 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 200,000 | 5 | 65.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 500,000 | 9 | 95.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 500,000 | 5 | 94.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 1,000,000 | 9 | 120.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 1,000,000 | 5 | 108.3 at α=8.25° | 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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