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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(oaf117-il) OAF117 AIRFOIL | ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord | Remove Airfoil details Airfoil plotter |
(oaf102-il) OAF102 AIRFOIL | ONERA/Aerospatiale OAF102 Fenestron airfoil Max thickness 10.2% at 28.7% chord Max camber 3.6% at 53.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oaf117-il,oaf102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf117-il | 50,000 | 9 | 28.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 9 | 46.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 5 | 49.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 9 | 64.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 5 | 63 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 9 | 84.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 5 | 78.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 9 | 96.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 5 | 89.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 50,000 | 9 | 40.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 50,000 | 5 | 41.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 9 | 61.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 5 | 60.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 9 | 82.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 5 | 77.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 9 | 107.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 5 | 86.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 9 | 114 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 5 | 92 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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