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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(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 |
(s805a-nr) NREL's S805A Airfoil | NREL HAWT airfoil S805A primary Max thickness 13.5% at 40% chord Max camber 2.1% at 35% chord | Remove Airfoil details Airfoil plotter |
(s3021-il) S3021-095-84 | Selig S3021 low Reynolds number airfoil Max thickness 9.5% at 30% chord Max camber 2.5% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(s4110-il) S4110 | Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord Max camber 3.1% at 45.4% chord | Remove Airfoil details Airfoil plotter |
(cast102-il) CAST 10-2/DOA 2 AIRFOIL | CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s828-nr,s805a-nr,s3021-il,s4110-il,cast102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| s805a-nr | 50,000 | 9 | 30.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 50,000 | 5 | 27.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 100,000 | 9 | 50.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 100,000 | 5 | 50.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 200,000 | 9 | 75.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 200,000 | 5 | 67 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 500,000 | 9 | 96.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 500,000 | 5 | 89.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 1,000,000 | 9 | 117.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 1,000,000 | 5 | 103.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 50,000 | 9 | 32.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 50,000 | 5 | 37.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 100,000 | 9 | 53.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 100,000 | 5 | 55.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 200,000 | 9 | 74.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 200,000 | 5 | 71.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 500,000 | 9 | 101.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 500,000 | 5 | 91.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 1,000,000 | 9 | 119.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 1,000,000 | 5 | 105.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 50,000 | 9 | 39.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 50,000 | 5 | 40.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 100,000 | 9 | 60.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 100,000 | 5 | 57.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 200,000 | 9 | 81.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 200,000 | 5 | 73.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 500,000 | 9 | 107.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 500,000 | 5 | 89.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4110-il | 1,000,000 | 9 | 122.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4110-il | 1,000,000 | 5 | 99.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 5 | 30.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 9 | 45.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 9 | 64 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 5 | 55.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 9 | 85.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 5 | 66.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 9 | 93.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 5 | 75.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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