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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(s102b-il) SOMERS S102 AIRFOIL (BLUNT) | Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2% at 68.7% chord | Remove Airfoil details Airfoil plotter |
(dae21-il) DAE-21 AIRFOIL | Drela DAE21 low Reynolds number airfoil Max thickness 11.8% at 32% chord Max camber 6.6% at 43.7% chord | Remove Airfoil details Airfoil plotter |
(s2055-il) S2055 | Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s102b-il,dae21-il,s2055-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s102b-il | 50,000 | 9 | 31.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 50,000 | 5 | 28.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 100,000 | 9 | 42.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 100,000 | 5 | 43.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 200,000 | 9 | 60.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 200,000 | 5 | 57.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 500,000 | 9 | 81.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 500,000 | 5 | 70.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 1,000,000 | 9 | 96.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 1,000,000 | 5 | 85.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 50,000 | 9 | 7.1 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 50,000 | 5 | 17.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 100,000 | 9 | 45.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 100,000 | 5 | 50.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 200,000 | 9 | 86.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 200,000 | 5 | 88.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 500,000 | 9 | 136.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 500,000 | 5 | 130.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 1,000,000 | 9 | 173.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 1,000,000 | 5 | 158.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 50,000 | 9 | 35.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 50,000 | 5 | 35.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 9 | 51.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 5 | 48.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 9 | 70.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 5 | 61.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 9 | 92.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 5 | 71.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 9 | 95.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 5 | 81 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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