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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(s8055-il) S8055 (12%) | Selig S8055 (12%) low Reynolds number airfoil Max thickness 12% at 33.9% chord Max camber 1.6% at 44.7% chord | Remove Airfoil details Airfoil plotter |
(s829-nr) NREL's S829 Airfoil | NREL HAWT airfoil S829 tip 16.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=0.70 Clmax(R)=0.68 Restrained max lift coef Max thickness 16% at 48.3% chord Max camber 0.7% at 48.3% chord | Remove Airfoil details Airfoil plotter |
(sm701-il) SM701 | Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord Max camber 3% at 60.3% chord | Remove Airfoil details Airfoil plotter |
(s9037-il) S9037 (9%) | Selig S9037 (9%) low Reynolds number airfoil used on the Opus R/C sailplane Max thickness 9% at 28.5% chord Max camber 3.3% at 42.4% chord | Remove Airfoil details Airfoil plotter |
(s801-nr) NREL's S801 Airfoil | NREL HAWT airfoil S801 primary 13.5% Not recommended Max thickness 13.5% at 37.8% chord Max camber 3.7% at 47.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s8055-il,s829-nr,sm701-il,s9037-il,s801-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8055-il | 50,000 | 9 | 32.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 50,000 | 5 | 32.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 100,000 | 9 | 50.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 100,000 | 5 | 48.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 200,000 | 9 | 71 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 200,000 | 5 | 62.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 500,000 | 9 | 86.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 500,000 | 5 | 74.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 1,000,000 | 9 | 95 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 1,000,000 | 5 | 88.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 50,000 | 9 | 22.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 50,000 | 5 | 21 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 100,000 | 9 | 33.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 100,000 | 5 | 25.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 200,000 | 9 | 47.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 200,000 | 5 | 35.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 500,000 | 9 | 63 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 500,000 | 5 | 62.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 1,000,000 | 9 | 88.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 1,000,000 | 5 | 72.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 50,000 | 9 | 27 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 50,000 | 5 | 30.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 9 | 50.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 5 | 46.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 9 | 68.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 5 | 64.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 9 | 95.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 5 | 79.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 9 | 110.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 5 | 93.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9037-il | 50,000 | 9 | 34.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9037-il | 50,000 | 5 | 39.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9037-il | 100,000 | 9 | 56.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9037-il | 100,000 | 5 | 57.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9037-il | 200,000 | 9 | 78.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9037-il | 200,000 | 5 | 74.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9037-il | 500,000 | 9 | 104.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9037-il | 500,000 | 5 | 95.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9037-il | 1,000,000 | 9 | 123.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9037-il | 1,000,000 | 5 | 110.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 50,000 | 9 | 31.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 50,000 | 5 | 27.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 100,000 | 9 | 52.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 100,000 | 5 | 52.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 200,000 | 9 | 85.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 200,000 | 5 | 80.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 500,000 | 9 | 118.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 500,000 | 5 | 112 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 1,000,000 | 9 | 147.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 1,000,000 | 5 | 133.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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