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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(defcnd1-il) DEFIANT CANARD BL20 AIRFOIL | Rutan DEFIANT canard BL20 airfoil Max thickness 20.9% at 28.6% chord Max camber 4.5% at 36.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (defcnd1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| defcnd1-il | 50,000 | 9 | 3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 50,000 | 5 | 6.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 100,000 | 9 | 4.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 100,000 | 5 | 32.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 200,000 | 9 | 52.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 200,000 | 5 | 60.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 500,000 | 9 | 93.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 500,000 | 5 | 92.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 1,000,000 | 9 | 124.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 1,000,000 | 5 | 116.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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