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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(s4061-il) S4061-096-84 | Selig S4061 low Reynolds number airfoil Max thickness 9.6% at 30.9% chord Max camber 3.3% at 44.7% 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 |
(s3021-il) S3021-095-84 | Selig S3021 low Reynolds number airfoil Max thickness 9.5% at 30% chord Max camber 2.5% at 39.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4061-il,s4096-il,s3021-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4061-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 50,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 100,000 | 9 | 59.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 100,000 | 5 | 60.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 200,000 | 9 | 84.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 200,000 | 5 | 81.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 500,000 | 9 | 116.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 500,000 | 5 | 105.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4061-il | 1,000,000 | 9 | 139.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4061-il | 1,000,000 | 5 | 121.2 at α=3.75° | 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 | |
| s3021-il | 50,000 | 9 | 32.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 50,000 | 5 | 37.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 100,000 | 9 | 53.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 100,000 | 5 | 55.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 200,000 | 9 | 74.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 200,000 | 5 | 71.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 500,000 | 9 | 101.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 500,000 | 5 | 91.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 1,000,000 | 9 | 119.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 1,000,000 | 5 | 105.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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