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 |
(b29tip-il) B-29 TIP AIRFOIL | Boeing B-29 tip airfoil Max thickness 9% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (davis-corrected-il,b29tip-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 | |
| b29tip-il | 50,000 | 9 | 34.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 50,000 | 5 | 34.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 5 | 50.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 9 | 68.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 5 | 66.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 9 | 91.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 5 | 84.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 9 | 106.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 5 | 90 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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