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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(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 |
(lwk80150k25-il) LWK 80-150/K25 | LWK 80-150/K25 symmetrical airfoil Max thickness 15% at 40.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca747a415-il) NACA 747A415 | NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nasasc2-0714-il,lwk80150k25-il,naca747a415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| lwk80150k25-il | 50,000 | 9 | 28 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 50,000 | 5 | 23.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 100,000 | 9 | 38.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 100,000 | 5 | 26.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 200,000 | 9 | 38.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 200,000 | 5 | 35.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 500,000 | 9 | 52.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 500,000 | 5 | 44 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80150k25-il | 1,000,000 | 9 | 59.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80150k25-il | 1,000,000 | 5 | 55.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 9 | 19 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 5 | 17 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 9 | 37.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 5 | 44.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 5 | 66.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 9 | 97.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 5 | 92.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 9 | 120.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 5 | 110.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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