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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(fx601261-il) WORTMANN FX 60-126/1 AIRFOIL | Wortmann FX 60-126/1 airfoil Max thickness 12.6% at 27.9% chord Max camber 4% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(fx72150b-il) WORTMANN FX 72-MS-150B AIRFOIL | Wortmann FX 72-MS-150B airfoil Max thickness 15% at 37.1% chord Max camber 9.7% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(la203a-il) DOUGLAS LA203A AIRFOIL | Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord | Remove Airfoil details Airfoil plotter |
(hs1712-il) HAM-STD HS1-712 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 12% at 36% chord Max camber 4.9% at 44% chord | Remove Airfoil details Airfoil plotter |
(goe173-il) GOE 173 (ALBATROS 6020) AIRFOIL | Gottingen 173 (Albatros 6020) airfoil Max thickness 7.8% at 20% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(oaf095-il) OAF095 AIRFOIL | ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx601261-il,fx72150b-il,la203a-il,hs1712-il,goe173-il,oaf095-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx601261-il | 50,000 | 9 | 34.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 50,000 | 5 | 39.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 100,000 | 9 | 59.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 100,000 | 5 | 60.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 200,000 | 9 | 82.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 200,000 | 5 | 76.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 500,000 | 9 | 108.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 500,000 | 5 | 84.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601261-il | 1,000,000 | 9 | 113.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601261-il | 1,000,000 | 5 | 88.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150b-il | 50,000 | 9 | 5.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150b-il | 50,000 | 5 | 9.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150b-il | 100,000 | 9 | 7.8 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150b-il | 100,000 | 5 | 39.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150b-il | 200,000 | 9 | 56.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150b-il | 200,000 | 5 | 76.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150b-il | 500,000 | 9 | 117.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150b-il | 500,000 | 5 | 117.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150b-il | 1,000,000 | 9 | 154.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150b-il | 1,000,000 | 5 | 151 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 50,000 | 9 | 6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 50,000 | 5 | 13.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 9 | 30.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 5 | 46.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 9 | 82.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 5 | 85.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 9 | 127.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 9 | 160.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 5 | 151.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 50,000 | 9 | 36.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 50,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 100,000 | 9 | 60.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 100,000 | 5 | 58.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 200,000 | 9 | 82.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 200,000 | 5 | 74.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 500,000 | 9 | 103.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 500,000 | 5 | 83.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1712-il | 1,000,000 | 9 | 103.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1712-il | 1,000,000 | 5 | 89.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 50,000 | 9 | 33.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 50,000 | 5 | 42.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 100,000 | 9 | 56.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 100,000 | 5 | 60.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 200,000 | 9 | 77.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 200,000 | 5 | 75.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 500,000 | 9 | 101.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 500,000 | 5 | 101.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 1,000,000 | 9 | 124.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 1,000,000 | 5 | 122.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 9 | 43.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 5 | 43.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 9 | 65.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 5 | 63.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 9 | 88.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 5 | 82.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 9 | 116.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 5 | 93.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 5 | 98.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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