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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(hor12-il) ONERA HOR12 AIRFOIL | Onera propeller blade airfoils from US Patent 4 Max thickness 11.9% at 22.8% chord Max camber 3.7% at 46.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hor12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hor12-il | 50,000 | 9 | 30.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 50,000 | 5 | 38 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 100,000 | 9 | 54.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 100,000 | 5 | 57.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 200,000 | 9 | 76.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 200,000 | 5 | 76.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 500,000 | 9 | 103.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 500,000 | 5 | 97.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 1,000,000 | 9 | 121.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 1,000,000 | 5 | 108.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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