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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(npl9615-il) NPL 9615 AIRFOIL | NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
(oa212-il) ONERA OA212 AIRFOIL | ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12% at 31.8% chord Max camber 2.3% at 31.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (npl9615-il,oa212-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9615-il | 50,000 | 9 | 29 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 5 | 30.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 9 | 43.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 5 | 42.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 9 | 56.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 9 | 70.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 5 | 68.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 9 | 84.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 5 | 77.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 50,000 | 9 | 26.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 50,000 | 5 | 31.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 100,000 | 9 | 44.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 100,000 | 5 | 45.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 200,000 | 9 | 60.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 200,000 | 5 | 59.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 500,000 | 9 | 82.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 500,000 | 5 | 76.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 1,000,000 | 9 | 96.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 1,000,000 | 5 | 87 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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