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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(goe265-il) GOE 265 AIRFOIL | Gottingen 265 airfoil Max thickness 7.7% at 14.9% chord Max camber 7.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(du8608418-il) DU86-084/18 8.44% | Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord Max camber 1% at 45.8% chord | Remove Airfoil details Airfoil plotter |
(naca000834-il) NACA 0008-34 | NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe265-il,du8608418-il,naca000834-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe265-il | 50,000 | 9 | 23 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe265-il | 50,000 | 5 | 39.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe265-il | 100,000 | 9 | 52.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe265-il | 100,000 | 5 | 61.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe265-il | 200,000 | 9 | 79.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe265-il | 200,000 | 5 | 82 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe265-il | 500,000 | 9 | 111.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe265-il | 500,000 | 5 | 109.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe265-il | 1,000,000 | 9 | 136.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe265-il | 1,000,000 | 5 | 129.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 50,000 | 9 | 32.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 50,000 | 5 | 31.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 100,000 | 9 | 46.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 100,000 | 5 | 43.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 200,000 | 9 | 63.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 200,000 | 5 | 53.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 500,000 | 9 | 75.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 500,000 | 5 | 59.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du8608418-il | 1,000,000 | 9 | 71 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du8608418-il | 1,000,000 | 5 | 70.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 50,000 | 9 | 18.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 50,000 | 5 | 18.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 100,000 | 9 | 24.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 100,000 | 5 | 30.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 200,000 | 9 | 40.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 200,000 | 5 | 36 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 500,000 | 9 | 57.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 500,000 | 5 | 37.4 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 1,000,000 | 9 | 43 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 1,000,000 | 5 | 42.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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