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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(s4095-il) S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) | Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 9.7% at 29.1% chord Max camber 1.7% at 33.7% chord | Remove Airfoil details Airfoil plotter |
(sc20706-il) NASA SC(2)-0706 AIRFOIL | NASA SC(2)-0706 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.6% at 82% chord | Remove Airfoil details Airfoil plotter |
(sd5060-il) SD5060 (9.5%) | Selig/Donovan SD5060 low Reynolds number airfoil Max thickness 9.5% at 24.9% chord Max camber 2% at 48.5% chord | Remove Airfoil details Airfoil plotter |
(s4083-il) S4083 (8%) | Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4095-il,sc20706-il,sd5060-il,s4083-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4095-il | 50,000 | 9 | 27.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4095-il | 50,000 | 5 | 32.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4095-il | 100,000 | 9 | 41.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4095-il | 100,000 | 5 | 43.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4095-il | 200,000 | 9 | 53.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4095-il | 200,000 | 5 | 53.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4095-il | 500,000 | 9 | 67.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4095-il | 500,000 | 5 | 65.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4095-il | 1,000,000 | 9 | 75.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4095-il | 1,000,000 | 5 | 72.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 50,000 | 9 | 24 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 50,000 | 5 | 25.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 100,000 | 9 | 38.2 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 100,000 | 5 | 33.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 200,000 | 9 | 40.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 200,000 | 5 | 44.1 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 500,000 | 9 | 67 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 500,000 | 5 | 55.8 at α=-0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 1,000,000 | 9 | 96.6 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 1,000,000 | 5 | 68 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd5060-il | 50,000 | 9 | 33.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd5060-il | 50,000 | 5 | 36.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd5060-il | 100,000 | 9 | 51.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd5060-il | 100,000 | 5 | 50.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd5060-il | 200,000 | 9 | 68.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd5060-il | 200,000 | 5 | 62.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd5060-il | 500,000 | 9 | 88.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd5060-il | 500,000 | 5 | 79.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd5060-il | 1,000,000 | 9 | 100.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd5060-il | 1,000,000 | 5 | 94.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 9 | 31.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 5 | 38.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 9 | 51.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 9 | 73.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 9 | 102.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 5 | 98.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 9 | 124.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 5 | 115.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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