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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(cap21c-il) CAP 21 (TraCFoil) | CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cap21c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cap21c-il | 50,000 | 9 | 9.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 50,000 | 5 | 14.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 100,000 | 9 | 17.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 100,000 | 5 | 26 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 200,000 | 9 | 38.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 200,000 | 5 | 48.1 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 500,000 | 9 | 74 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 500,000 | 5 | 77.6 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 1,000,000 | 9 | 97.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 1,000,000 | 5 | 97.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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