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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(s813-nr) NREL's S813 Airfoil | NREL HAWT airfoil S813 tip Max thickness 16% at 40.4% chord Max camber 2.3% at 54.4% chord | Remove Airfoil details Airfoil plotter |
(pt40-il) PT40 | Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% chord | Remove Airfoil details Airfoil plotter |
(s809-nr) NREL's S809 Airfoil | NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s813-nr,pt40-il,s809-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s813-nr | 50,000 | 9 | 23.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 50,000 | 5 | 20.4 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 100,000 | 9 | 35.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 100,000 | 5 | 34.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 200,000 | 9 | 64.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 200,000 | 5 | 65.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 500,000 | 9 | 104.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 500,000 | 5 | 96.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 1,000,000 | 9 | 130.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 1,000,000 | 5 | 115.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 9 | 32.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 9 | 48.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 5 | 46.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 9 | 64.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 5 | 57.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 9 | 78.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 9 | 95 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 5 | 89.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 50,000 | 9 | 15.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 50,000 | 5 | 13.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 9 | 23.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 5 | 26.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 5 | 53.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 9 | 81.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 5 | 75.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 9 | 100.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 5 | 89.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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