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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(s5010-il) S5010 | Selig S5010 low Reynolds number airfoil Max thickness 9.8% at 27.6% chord Max camber 1.8% at 32% chord | Remove Airfoil details Airfoil plotter |
(s8036-il) S8036 (16%) | Selig S8036 low Reynolds number airfoil Max thickness 16% at 36.8% chord Max camber 1.3% at 40.4% 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 |
(s7075-il) S7075 (9%) | Selig S7075 low Reynolds number airfoil Max thickness 9% at 29% chord Max camber 2.8% at 46.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s5010-il,s8036-il,s829-nr,s7075-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s5010-il | 50,000 | 9 | 24.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 50,000 | 5 | 32.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 9 | 45 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 5 | 47.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 9 | 63.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 5 | 62.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 9 | 86.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 5 | 80.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 9 | 102.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 5 | 94.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 50,000 | 9 | 26.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 50,000 | 5 | 25.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 100,000 | 9 | 48.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 100,000 | 5 | 48 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 200,000 | 9 | 70.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 200,000 | 5 | 61.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 500,000 | 9 | 87.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 500,000 | 5 | 73.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 1,000,000 | 9 | 99.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 1,000,000 | 5 | 82.1 at α=7.5° | 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 | |
| s7075-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 50,000 | 5 | 40.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 100,000 | 9 | 59.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 100,000 | 5 | 57.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 200,000 | 9 | 81.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 200,000 | 5 | 74 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 500,000 | 9 | 108 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 500,000 | 5 | 91.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 1,000,000 | 9 | 123 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 1,000,000 | 5 | 101.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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