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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(sc20414-il) NASA SC(2)-0414 AIRFOIL | NASA SC(2)-0414 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 1.5% at 83% 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 |
(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 |
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Polars for (sc20414-il,s4310-il,sc2110-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20414-il | 50,000 | 9 | 25.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 50,000 | 5 | 21.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 100,000 | 9 | 25.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 100,000 | 5 | 30.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 200,000 | 9 | 35.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 200,000 | 5 | 43.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 500,000 | 9 | 57.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 500,000 | 5 | 63.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 1,000,000 | 9 | 76.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 1,000,000 | 5 | 78.8 at α=8.25° | 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 | |
| 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 | |
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