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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(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 |
(ea61009-il) EPPLER EA 6(-1)-009 AIRFOIL | Eppler EA 6(-1)-009 airfoil Max thickness 9% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(hs1712-il) HAM-STD HS1-712 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 12% at 36% chord Max camber 4.9% at 44% chord | Remove Airfoil details Airfoil plotter |
(goe08k-il) GOE 8K AIRFOIL | Gottingen 8K airfoil Max thickness 14.9% at 50% chord Max camber 6.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hs1404-il,ea61009-il,hs1712-il,goe08k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| ea61009-il | 50,000 | 9 | 23.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 50,000 | 5 | 21.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 100,000 | 9 | 29.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 100,000 | 5 | 27.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 200,000 | 9 | 31.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 200,000 | 5 | 33.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 500,000 | 9 | 46.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 500,000 | 5 | 58.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 1,000,000 | 9 | 72.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 1,000,000 | 5 | 76 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 50,000 | 9 | 36.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 50,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 100,000 | 9 | 60.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 100,000 | 5 | 58.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 200,000 | 9 | 82.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 200,000 | 5 | 74.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 500,000 | 9 | 103.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 500,000 | 5 | 83.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 1,000,000 | 9 | 103.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 1,000,000 | 5 | 89.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe08k-il | 50,000 | 9 | 18 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe08k-il | 50,000 | 5 | 15.7 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe08k-il | 100,000 | 9 | 26.9 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe08k-il | 100,000 | 5 | 24.1 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe08k-il | 200,000 | 9 | 44.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe08k-il | 200,000 | 5 | 43.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe08k-il | 500,000 | 9 | 103.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe08k-il | 500,000 | 5 | 96.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe08k-il | 1,000,000 | 9 | 143.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe08k-il | 1,000,000 | 5 | 122 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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