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 |
(s1210-il) S1210 12% | Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord | Remove Airfoil details Airfoil plotter |
(fx60160-il) FX 60-160 AIRFOIL | Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord | Remove Airfoil details Airfoil plotter |
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Polars for (defcnd1-il,s1210-il,fx60160-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 | |
| s1210-il | 50,000 | 9 | 14.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 50,000 | 5 | 42.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 100,000 | 9 | 59.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 100,000 | 5 | 66 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 200,000 | 9 | 86.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 200,000 | 5 | 88 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 500,000 | 9 | 121.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 500,000 | 5 | 115 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 1,000,000 | 9 | 148 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 1,000,000 | 5 | 135.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 50,000 | 9 | 23.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 50,000 | 5 | 22.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 100,000 | 9 | 51 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 100,000 | 5 | 48.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 200,000 | 9 | 72.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 500,000 | 9 | 96.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 500,000 | 5 | 89 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 1,000,000 | 9 | 116.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 1,000,000 | 5 | 102.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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