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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(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL | Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (davis-corrected-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| davis-corrected-il | 50,000 | 9 | 12.5 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 100,000 | 9 | 36.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 200,000 | 9 | 63.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 500,000 | 9 | 96.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 1,000,000 | 9 | 122.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 2,000,000 | 9 | 137.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 5,000,000 | 9 | 157.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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