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 |
(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) | NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord | Remove Airfoil details Airfoil plotter |
(s1016-il) S1016 | Selig S1016 HPV airfoil Max thickness 17.5% at 41.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(oa206-il) ONERA OA206 AIRFOIL | ONERA/Aerospatiale OA206 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 6% at 31.8% chord Max camber 0.8% at 19.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oaf117-il,nasasc2-0714-il,s1016-il,oa206-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 | |
| nasasc2-0714-il | 50,000 | 9 | 24.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 50,000 | 5 | 22.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 9 | 28.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 5 | 31.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 9 | 36.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 5 | 43.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 9 | 66 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 5 | 64 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 9 | 83.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 5 | 80 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 50,000 | 9 | 28.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 50,000 | 5 | 22.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 9 | 39.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 5 | 23.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 9 | 35.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 5 | 30.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 9 | 40.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 5 | 41.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 9 | 52.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 5 | 52 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 50,000 | 9 | 27.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 100,000 | 9 | 36.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 100,000 | 5 | 35.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 200,000 | 9 | 46.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 200,000 | 5 | 44.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 500,000 | 9 | 58.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 500,000 | 5 | 56.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa206-il | 1,000,000 | 9 | 67.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa206-il | 1,000,000 | 5 | 69.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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