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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(s9027-il) S9027 (8%) | Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s818-nr) NREL's S818 Airfoil | NREL HAWT airfoil S818 root 24.0% Dia=30 to 50 m Re=2.5E+6 Clmax(S)=1.68 Clmax(R)=1.61 Restrained max lift coef Max thickness 24% at 30.9% chord Max camber 3.3% at 74.2% chord | Remove Airfoil details Airfoil plotter |
(s4310-il) S4310 | Selig S4310 low Reynolds number airfoil Max thickness 10.9% at 30.7% chord Max camber 4.2% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(s822-nr) NREL's S822 Airfoil | NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord Max camber 1.8% at 59.5% chord | Remove Airfoil details Airfoil plotter |
(s816-nr) NREL's S816 Airfoil | NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef Max thickness 21% at 39% chord Max camber 1.8% at 67.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s9027-il,s818-nr,s4310-il,s822-nr,s816-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s9027-il | 50,000 | 9 | 22.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 50,000 | 5 | 23.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 9 | 30.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 5 | 32.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 9 | 40.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 5 | 43.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 9 | 57.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 5 | 59.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 9 | 71.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 5 | 73.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 50,000 | 9 | 6.8 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 50,000 | 5 | 11.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 100,000 | 9 | 16.7 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 100,000 | 5 | 39.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 200,000 | 9 | 57.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 200,000 | 5 | 58.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 500,000 | 9 | 83.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 500,000 | 5 | 81.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 1,000,000 | 9 | 105.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 1,000,000 | 5 | 101.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 50,000 | 9 | 28.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 50,000 | 5 | 36.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 100,000 | 9 | 56.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 100,000 | 5 | 58.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 200,000 | 9 | 81 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 200,000 | 5 | 78.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 500,000 | 9 | 112.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 500,000 | 5 | 102.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 1,000,000 | 9 | 134.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 1,000,000 | 5 | 117.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 50,000 | 9 | 27.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 50,000 | 5 | 23.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 9 | 42.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 9 | 68.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 5 | 60.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 9 | 94.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 5 | 85.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 9 | 117.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 5 | 96.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 50,000 | 9 | 16.9 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 50,000 | 5 | 12.9 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 100,000 | 9 | 21 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 100,000 | 5 | 22.2 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 200,000 | 9 | 59 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 200,000 | 5 | 60.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 500,000 | 9 | 96.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 500,000 | 5 | 91 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 1,000,000 | 9 | 121.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 1,000,000 | 5 | 108.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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