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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(s9000-il) S9000 (9%) | Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 28.2% chord Max camber 2.1% at 44.8% chord | Remove Airfoil details Airfoil plotter |
(s820-nr) NREL's S820 Airfoil | NREL HAWT airfoil S820 tip 16.0% Dia=10 to 20 m Re=1.3E+6 Clmax(S)=1.10 Clmax(R)=1.06 Restrained max lift coef Max thickness 16% at 45.1% chord Max camber 2.1% at 59.7% chord | Remove Airfoil details Airfoil plotter |
(s828-nr) NREL's S828 Airfoil | NREL HAWT airfoil S828 tip 16.0% Dia=40 to 50 m Re=3.0E+6 Clmax(S)=0.90 Clmax(R)=0.89 Restrained max lift coef Max thickness 16% at 47.1% chord Max camber 2.2% at 47.1% chord | Remove Airfoil details Airfoil plotter |
(s818-nr) NREL's S818 Airfoil | NREL HAWT airfoil S818 root 24.0% Dia=30 to 50 m Re=2.5E+6 Clmax(S)=1.68 Clmax(R)=1.61 Restrained max lift coef Max thickness 24% at 30.9% chord Max camber 3.3% at 74.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s9000-il,s820-nr,s828-nr,s818-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s9000-il | 50,000 | 9 | 34.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9000-il | 50,000 | 5 | 37.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9000-il | 100,000 | 9 | 53.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9000-il | 100,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9000-il | 200,000 | 9 | 71 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9000-il | 200,000 | 5 | 66.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9000-il | 500,000 | 9 | 93 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9000-il | 500,000 | 5 | 84.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9000-il | 1,000,000 | 9 | 108.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9000-il | 1,000,000 | 5 | 97.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 50,000 | 9 | 26.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 50,000 | 5 | 22.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 100,000 | 9 | 39.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 100,000 | 5 | 37 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 200,000 | 9 | 65.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 200,000 | 5 | 65.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 500,000 | 9 | 105.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 500,000 | 5 | 95.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 1,000,000 | 9 | 129.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 1,000,000 | 5 | 109.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 50,000 | 9 | 19.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 50,000 | 5 | 18.1 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 100,000 | 9 | 28.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 100,000 | 5 | 28.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 200,000 | 9 | 63.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 200,000 | 5 | 40.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 500,000 | 9 | 76.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 500,000 | 5 | 82 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 1,000,000 | 9 | 112.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 1,000,000 | 5 | 107 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 50,000 | 9 | 6.8 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 50,000 | 5 | 11.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 100,000 | 9 | 16.7 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 100,000 | 5 | 39.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 200,000 | 9 | 57.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 200,000 | 5 | 58.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 500,000 | 9 | 83.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 500,000 | 5 | 81.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 1,000,000 | 9 | 105.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 1,000,000 | 5 | 101.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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