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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(s8035-il) S8035 for RC aerobatic 14% thick | Selig S8035 low Reynolds number airfoil Max thickness 14% at 29.1% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s835-nr) NREL's S835 Airfoil | NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef Max thickness 21% at 30.5% chord Max camber 2.4% at 78% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s8035-il,s835-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8035-il | 50,000 | 9 | 24.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 50,000 | 5 | 27.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 100,000 | 9 | 38.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 100,000 | 5 | 39.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 200,000 | 9 | 52 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 200,000 | 5 | 51.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 500,000 | 9 | 70.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 500,000 | 5 | 66.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8035-il | 1,000,000 | 9 | 83.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8035-il | 1,000,000 | 5 | 78.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 50,000 | 9 | 23.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 50,000 | 5 | 19.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 100,000 | 9 | 34.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 100,000 | 5 | 35.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 200,000 | 9 | 55.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 200,000 | 5 | 51.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 500,000 | 9 | 77.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 500,000 | 5 | 65.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 1,000,000 | 9 | 88.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 1,000,000 | 5 | 70.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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