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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(usnps4-il) USNPS4 (smoothed) | Jacobs USNPS4 (smoothed) 17.5 kW wind turbine airfoil Max thickness 11.9% at 34.2% chord Max camber 5% at 34.2% chord | Remove Airfoil details Airfoil plotter |
(ag18-il) AG18 | Drela AG18 airfoil Max thickness 5.9% at 20.7% chord Max camber 2.2% at 44.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usnps4-il,ag18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usnps4-il | 50,000 | 9 | 32.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 50,000 | 5 | 37.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 100,000 | 9 | 55.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 100,000 | 5 | 53.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 200,000 | 9 | 74.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 200,000 | 5 | 67.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 500,000 | 9 | 95.2 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 500,000 | 5 | 87.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usnps4-il | 1,000,000 | 9 | 110.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usnps4-il | 1,000,000 | 5 | 105.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 50,000 | 9 | 35.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 50,000 | 5 | 36.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 9 | 50.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 5 | 48.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 9 | 65.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 9 | 81.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 5 | 77 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 9 | 95.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 5 | 90.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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