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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(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 |
(e472-il) EPPLER 472 AIRFOIL | Eppler E472 aerobatic aircraft airfoil Max thickness 12.1% at 17.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hs1712-il,e472-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| e472-il | 50,000 | 9 | 17.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e472-il | 50,000 | 5 | 21.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e472-il | 100,000 | 9 | 26.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e472-il | 100,000 | 5 | 33.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e472-il | 200,000 | 9 | 41.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e472-il | 200,000 | 5 | 49.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e472-il | 500,000 | 9 | 69.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e472-il | 500,000 | 5 | 72.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e472-il | 1,000,000 | 9 | 91.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e472-il | 1,000,000 | 5 | 90.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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