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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(aquilasm-il) AQUILA 9.3% smoothed | AQUILA R/C sailplane airfoil Max thickness 9.4% at 31.3% chord Max camber 4% at 34.7% chord | Remove Airfoil details Airfoil plotter |
(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 |
(s819-nr) NREL's S819 Airfoil | NREL HAWT airfoil S819 primary 21.0% Dia=10 to 20 m Re=1.0E+6 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.1% at 28.4% chord Max camber 1.3% at 77.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (aquilasm-il,s9027-il,s819-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| aquilasm-il | 50,000 | 9 | 25.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 50,000 | 5 | 37 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 100,000 | 9 | 51.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 100,000 | 5 | 56.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 200,000 | 9 | 74.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 200,000 | 5 | 75 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 500,000 | 9 | 104.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 500,000 | 5 | 99.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| aquilasm-il | 1,000,000 | 9 | 127.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| aquilasm-il | 1,000,000 | 5 | 118.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| s819-nr | 50,000 | 9 | 7.9 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s819-nr | 50,000 | 5 | 22.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s819-nr | 100,000 | 9 | 38.4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s819-nr | 100,000 | 5 | 40.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s819-nr | 200,000 | 9 | 55.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s819-nr | 200,000 | 5 | 54.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s819-nr | 500,000 | 9 | 77.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s819-nr | 500,000 | 5 | 72.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s819-nr | 1,000,000 | 9 | 93.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s819-nr | 1,000,000 | 5 | 84.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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