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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(fx73170a-il) WORTMANN FX 73-170 A | Wortmann FX 73-170 A airfoil Max thickness 17.1% at 43.5% chord Max camber 5.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(e604-il) EPPLER 604 AIRFOIL | Eppler E604 sailplane airfoil Max thickness 18.8% at 37.3% chord Max camber 3.4% at 42.3% 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 |
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Polars for (fx73170a-il,e604-il,du8608418-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73170a-il | 50,000 | 9 | 4.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 50,000 | 5 | 11.1 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 100,000 | 9 | 18.1 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 100,000 | 5 | 17.4 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 200,000 | 9 | 31.2 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 200,000 | 5 | 51.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 500,000 | 9 | 117.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 500,000 | 5 | 110.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 1,000,000 | 9 | 151.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 1,000,000 | 5 | 144 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 50,000 | 9 | 5.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 50,000 | 5 | 13.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 100,000 | 9 | 34.1 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 100,000 | 5 | 30.1 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 200,000 | 9 | 65.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 200,000 | 5 | 67.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 500,000 | 9 | 106.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 500,000 | 5 | 101.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 1,000,000 | 9 | 136.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 1,000,000 | 5 | 123.8 at α=5° | 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 | |
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