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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(s5020-il) S5020 | Selig S5020 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.2% at 27.8% chord | Remove Airfoil details Airfoil plotter |
(sc2110-il) SIKORSKY SC2110 AIRFOIL | Sikorsky/Lednicer & Owen SC2110 rotorcraft airfoil (SC5410) Max thickness 9.9% at 37.7% chord Max camber 1.9% at 15.7% chord | Remove Airfoil details Airfoil plotter |
(s4180-il) S4180-098-84 | Selig S4180 low Reynolds number airfoil Max thickness 9.8% at 26.1% chord Max camber 4% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(sokolov-il) SOKOLOV AIRFOIL | Sokolov R/C sailplane airfoil Max thickness 7.1% at 25% chord Max camber 6.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(s4233-il) S4233-136-84 | Selig S4233 low Reynolds number airfoil Max thickness 13.6% at 34.9% chord Max camber 2.7% at 48.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s5020-il,sc2110-il,s4180-il,sokolov-il,s4233-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s5020-il | 50,000 | 9 | 25.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 50,000 | 5 | 33.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 100,000 | 9 | 46 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 100,000 | 5 | 48.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 200,000 | 9 | 64.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 200,000 | 5 | 63.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 500,000 | 9 | 88 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 500,000 | 5 | 82.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 1,000,000 | 9 | 104.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 1,000,000 | 5 | 96.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 50,000 | 9 | 26.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 50,000 | 5 | 27.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 100,000 | 9 | 34.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 100,000 | 5 | 38.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 200,000 | 9 | 47.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 200,000 | 5 | 52.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 500,000 | 9 | 71.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 500,000 | 5 | 74.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 1,000,000 | 9 | 91.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 1,000,000 | 5 | 92.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 50,000 | 9 | 28.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 50,000 | 5 | 37.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 100,000 | 9 | 55.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 100,000 | 5 | 58.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 200,000 | 9 | 78.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 200,000 | 5 | 78.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 500,000 | 9 | 110.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 500,000 | 5 | 104.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 1,000,000 | 9 | 133.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 1,000,000 | 5 | 122.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sokolov-il | 50,000 | 9 | 44.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sokolov-il | 50,000 | 5 | 45.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sokolov-il | 100,000 | 9 | 68.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sokolov-il | 100,000 | 5 | 69.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sokolov-il | 200,000 | 9 | 92.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sokolov-il | 200,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sokolov-il | 500,000 | 9 | 124.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sokolov-il | 500,000 | 5 | 118.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sokolov-il | 1,000,000 | 9 | 146.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sokolov-il | 1,000,000 | 5 | 109.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 50,000 | 9 | 22.6 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 50,000 | 5 | 26.1 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 100,000 | 9 | 52.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 100,000 | 5 | 54.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 200,000 | 9 | 77.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 200,000 | 5 | 77 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 500,000 | 9 | 111.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 500,000 | 5 | 104.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4233-il | 1,000,000 | 9 | 136 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4233-il | 1,000,000 | 5 | 121.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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