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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(isa571-il) I.S.A. 571 | I.S.A. 571 airfoil Max thickness 7.4% at 30% chord Max camber 3.6% at 30% chord | Remove Airfoil details Airfoil plotter |
(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 |
(naca16006-il) NACA 16-006 | NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe443-il) GOE 443 AIRFOIL | Gottingen 443 airfoil Max thickness 5% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(isa962-il) I.S.A. 962 | I.S.A. 962 airfoil Max thickness 9.6% at 20% chord Max camber 4.6% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (isa571-il,defcnd1-il,naca16006-il,goe443-il,isa962-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| isa571-il | 50,000 | 9 | 35.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 50,000 | 5 | 39.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 100,000 | 9 | 51.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 100,000 | 5 | 54.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 200,000 | 9 | 69.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 200,000 | 5 | 70.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 500,000 | 9 | 93.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 500,000 | 5 | 89.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa571-il | 1,000,000 | 9 | 109.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa571-il | 1,000,000 | 5 | 100.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| naca16006-il | 50,000 | 9 | 16.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 50,000 | 5 | 16.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 100,000 | 9 | 20.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 100,000 | 5 | 21.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 200,000 | 9 | 25.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 200,000 | 5 | 33.4 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 500,000 | 9 | 41.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 500,000 | 5 | 34 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16006-il | 1,000,000 | 9 | 40.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16006-il | 1,000,000 | 5 | 36.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 50,000 | 9 | 16.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 50,000 | 5 | 16 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 100,000 | 9 | 20.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 100,000 | 5 | 26.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 200,000 | 9 | 34 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 200,000 | 5 | 32.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 500,000 | 9 | 44.5 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 500,000 | 5 | 32 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe443-il | 1,000,000 | 9 | 43.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe443-il | 1,000,000 | 5 | 60.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 50,000 | 9 | 36.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 50,000 | 5 | 39.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 100,000 | 9 | 57.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 100,000 | 5 | 56.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 200,000 | 9 | 77.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 200,000 | 5 | 69.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 500,000 | 9 | 98.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 500,000 | 5 | 88.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 1,000,000 | 9 | 111.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 1,000,000 | 5 | 102.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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