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 |
(s4096-il) S4096 (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 12.5% at 34% chord Max camber 1.2% at 34% chord | Remove Airfoil details Airfoil plotter |
(s833-nr) NREL's S833 Airfoil | NREL HAWT airfoil S833 primary 18.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.10 Clmax(R)=1.13 High max lift coef Max thickness 18% at 36.3% chord Max camber 2.5% at 78.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4095-il,s4096-il,s833-nr)
| 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 | |
| s4096-il | 50,000 | 9 | 27.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 50,000 | 5 | 31.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 100,000 | 9 | 39.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 100,000 | 5 | 40.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 200,000 | 9 | 49 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 200,000 | 5 | 48.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 500,000 | 9 | 59.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 500,000 | 5 | 57.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 1,000,000 | 9 | 65.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 1,000,000 | 5 | 63.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 50,000 | 9 | 27.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 50,000 | 5 | 23.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 100,000 | 9 | 39.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 100,000 | 5 | 36.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 200,000 | 9 | 54.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 200,000 | 5 | 55.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 500,000 | 9 | 86.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 500,000 | 5 | 74.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 1,000,000 | 9 | 104.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 1,000,000 | 5 | 79.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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