Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(fx66s161-il) FX 66-S-161 AIRFOIL | Wortmann FX 66-S-161 airfoil Max thickness 16.1% at 33.9% chord Max camber 3.9% at 43.5% 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 |
(e395-il) EPPLER 395 AIRFOIL | Eppler E395 human e664ered aircraft airfoil Max thickness 12.3% at 29.5% chord Max camber 5.2% at 52.3% 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 |
Drawing Options
Polars for (fx66s161-il,du8608418-il,e395-il,naca000834-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66s161-il | 50,000 | 9 | 5.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 50,000 | 5 | 16.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 9 | 16.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 5 | 42.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 9 | 73.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 5 | 75.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 9 | 116 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 5 | 114.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 9 | 148.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 5 | 134.5 at α=7.25° | 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 | |
| e395-il | 50,000 | 9 | 31 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 50,000 | 5 | 28.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 100,000 | 9 | 59.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 100,000 | 5 | 61.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 200,000 | 9 | 92.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 200,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 500,000 | 9 | 136.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 500,000 | 5 | 128.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 9 | 169.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 5 | 144.1 at α=4° | 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 | |
| Reynolds number calculator | |||||||