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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(rg15-il) RG-15 8.9% | Rolf Girsberger RG 15 low Reynolds number airfoil Max thickness 8.9% at 30.2% chord Max camber 1.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(s1048-il) S1048 14% (Danny Howell) | Selig S1048 airfoil Max thickness 14% at 27% 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 |
(s6062-il) S6062 8% | Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord | Remove Airfoil details Airfoil plotter |
(rc08b3-il) NASA/LANGLEY RC-08(B)3 AIRFOIL | NASA/Langley RC-08(B)3 rotorcraft airfoil Max thickness 8% at 37.8% chord Max camber 1.1% at 34.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg15-il,s1048-il,s835-nr,s6062-il,rc08b3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg15-il | 50,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 50,000 | 5 | 36.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 100,000 | 9 | 52.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 100,000 | 5 | 50.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 200,000 | 9 | 68.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 200,000 | 5 | 63.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 500,000 | 9 | 89 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 500,000 | 5 | 79 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 1,000,000 | 9 | 102.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 1,000,000 | 5 | 88.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 50,000 | 9 | 24.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 50,000 | 5 | 28.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 100,000 | 9 | 40.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 100,000 | 5 | 41.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 200,000 | 9 | 56 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 200,000 | 5 | 54.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 500,000 | 9 | 75.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 500,000 | 5 | 66.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1048-il | 1,000,000 | 9 | 83.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1048-il | 1,000,000 | 5 | 72.8 at α=6.5° | 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 | |
| s6062-il | 50,000 | 9 | 34.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 50,000 | 5 | 35.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 100,000 | 9 | 50.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 100,000 | 5 | 48.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 200,000 | 9 | 65.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 200,000 | 5 | 58.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 500,000 | 9 | 82 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 500,000 | 5 | 68.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 1,000,000 | 9 | 91 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 1,000,000 | 5 | 73.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 50,000 | 9 | 32.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 50,000 | 5 | 31.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 100,000 | 9 | 45.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 100,000 | 5 | 41.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 200,000 | 9 | 57.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 200,000 | 5 | 49.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 500,000 | 9 | 67.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 500,000 | 5 | 60 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 1,000,000 | 9 | 71.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 1,000,000 | 5 | 73.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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