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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(hor20-il) ONERA HOR20 AIRFOIL | Onera propeller blade airfoils from US Patent 4 Max thickness 20.4% at 24.3% chord Max camber 3.3% at 51.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hor20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hor20-il | 50,000 | 9 | 4.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 50,000 | 5 | 21.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 100,000 | 9 | 34.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 100,000 | 5 | 44.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 200,000 | 9 | 61.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 200,000 | 5 | 63.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 500,000 | 9 | 91.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 500,000 | 5 | 83.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 1,000,000 | 9 | 112.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 1,000,000 | 5 | 99.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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