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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(oa209-il) ONERA OA209 AIRFOIL | ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 9% at 29.3% chord Max camber 1.6% at 17.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oa209-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oa209-il | 50,000 | 9 | 25.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 50,000 | 5 | 28.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 100,000 | 9 | 36 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 100,000 | 5 | 41.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 200,000 | 5 | 55.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 500,000 | 9 | 75.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 500,000 | 5 | 73.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa209-il | 1,000,000 | 9 | 90.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa209-il | 1,000,000 | 5 | 85.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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