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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(davissm-il) davissm | Davis 3R F1B free flight airfoil (smoothed) Max thickness 5.9% at 30.6% chord Max camber 5.9% at 45.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (davissm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| davissm-il | 50,000 | 9 | 45.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 50,000 | 5 | 45.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 100,000 | 9 | 70.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 100,000 | 5 | 69.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 200,000 | 9 | 96.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 200,000 | 5 | 92.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 500,000 | 9 | 131.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 500,000 | 5 | 118.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 1,000,000 | 9 | 154.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 1,000,000 | 5 | 128.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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