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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(raf34-il) RAF 34 AIRFOIL | RAF-34 airfoil Max thickness 12.6% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
(s830-nr) NREL's S830 Airfoil | NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef Max thickness 21% at 38.4% chord Max camber 4.4% at 70.5% chord | Remove Airfoil details Airfoil plotter |
(fg4-il) Fage & Collins 4 | Fage & Collins 4 airfoil Max thickness 12.7% at 30% chord Max camber 4.7% at 30% chord | Remove Airfoil details Airfoil plotter |
(fg3-il) Fage & Collins 3 | Fage & Collins 3 airfoil Max thickness 10.1% at 30% chord Max camber 4.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(daytonwright6-il) Dayton-Wright 6 | Dayton-Wright 6 airfoil Max thickness 13.6% at 30% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf34-il,s830-nr,fg4-il,fg3-il,daytonwright6-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf34-il | 50,000 | 9 | 25.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 50,000 | 5 | 30.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 100,000 | 9 | 48.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 100,000 | 5 | 49.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 200,000 | 9 | 67.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 200,000 | 5 | 65.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 500,000 | 9 | 90.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 500,000 | 5 | 79.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 1,000,000 | 9 | 99.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 1,000,000 | 5 | 84.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 50,000 | 9 | 4.2 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 50,000 | 5 | 10.8 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 100,000 | 9 | 17.7 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 100,000 | 5 | 34.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 200,000 | 9 | 61.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 200,000 | 5 | 66.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 500,000 | 9 | 95.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 500,000 | 5 | 94 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 1,000,000 | 9 | 117.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 1,000,000 | 5 | 115.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 50,000 | 9 | 30.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 50,000 | 5 | 32.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 100,000 | 9 | 51.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 100,000 | 5 | 47.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 200,000 | 9 | 65.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 200,000 | 5 | 47 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 500,000 | 9 | 62.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 500,000 | 5 | 58.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 1,000,000 | 9 | 71.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 1,000,000 | 5 | 72.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 50,000 | 9 | 32.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 50,000 | 5 | 35.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 100,000 | 9 | 48.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 100,000 | 5 | 49.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 200,000 | 9 | 65.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 200,000 | 5 | 65.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 500,000 | 9 | 90.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 500,000 | 5 | 89 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 1,000,000 | 9 | 111.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 1,000,000 | 5 | 108.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 50,000 | 9 | 11 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 50,000 | 5 | 31.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 100,000 | 9 | 45.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 100,000 | 5 | 49.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 200,000 | 9 | 66.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 200,000 | 5 | 66.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 500,000 | 9 | 92.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 500,000 | 5 | 89.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 1,000,000 | 9 | 115.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 1,000,000 | 5 | 111.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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