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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(naca0024-il) NACA 0024 | NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca66-018-il) NACA 66-018 | NACA 66-018 airfoil Max thickness 18% at 45% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe391-il) GOE 391 AIRFOIL | Gottingen 391 airfoil Max thickness 5.1% at 40% chord Max camber 3.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe229-il) GOE 229 (MVA H.39) AIRFOIL | Gottingen 229 (MVA H.39) airfoil Max thickness 19.3% at 29% chord Max camber 5.9% at 49.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca0024-il,naca66-018-il,goe391-il,goe229-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0024-il | 50,000 | 9 | 15.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 50,000 | 5 | 21.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 9 | 34.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 5 | 30.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 9 | 43 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 5 | 37 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 9 | 52.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 5 | 50.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 9 | 68.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 5 | 64.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 50,000 | 9 | 20.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 50,000 | 5 | 15.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 9 | 31.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 5 | 18.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 9 | 31 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 5 | 34.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 9 | 57.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 5 | 50.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 9 | 72 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 5 | 57.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 50,000 | 9 | 39.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 50,000 | 5 | 41.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 100,000 | 9 | 58.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 100,000 | 5 | 58.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 200,000 | 5 | 75.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 200,000 | 0 | 84.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 500,000 | 9 | 106 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 500,000 | 5 | 84.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 1,000,000 | 9 | 104.7 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 1,000,000 | 5 | 86.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 9 | 10.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 5 | 21.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 9 | 45.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 5 | 38.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 9 | 53.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 5 | 40.9 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 9 | 54.8 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 5 | 47.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 9 | 59.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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