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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(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 |
(ua79sff-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT | University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP Max thickness 8.7% at 73.1% chord Max camber 3.4% at 78.1% chord | Remove Airfoil details Airfoil plotter |
(goe610bm-il) GOE 610-B MOD. AIRFOIL | Gottingen 610-B MOD airfoil Max thickness 7.7% at 30% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe394-il) GOE 394 AIRFOIL | Gottingen 394 airfoil Max thickness 6.1% at 19.9% chord Max camber 5.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sokolov-il,ua79sff-il,goe610bm-il,goe394-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| ua79sff-il | 50,000 | 9 | 3.4 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 50,000 | 5 | 3.5 at α=19.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 9 | 3.6 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 5 | 4.1 at α=18.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 9 | 3.8 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 5 | 5.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 9 | 6.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 5 | 25.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 5 | 62 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 50,000 | 9 | 40.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 50,000 | 5 | 43.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 100,000 | 9 | 62.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 100,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 200,000 | 9 | 83.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 200,000 | 5 | 82.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 500,000 | 9 | 110.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 500,000 | 5 | 107.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe610bm-il | 1,000,000 | 9 | 130.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe610bm-il | 1,000,000 | 5 | 125 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 50,000 | 9 | 40.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 50,000 | 5 | 44.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 100,000 | 9 | 64.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 100,000 | 5 | 66.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 200,000 | 9 | 90.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 200,000 | 5 | 85.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 500,000 | 9 | 116.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 500,000 | 5 | 108 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe394-il | 1,000,000 | 9 | 139.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe394-il | 1,000,000 | 5 | 112.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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