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 |
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Polars for (sokolov-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 | |
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