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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(goe679-il) GOE 679 AIRFOIL | Gottingen 679 airfoil Max thickness 18.3% at 29.1% chord Max camber 4.5% at 39.1% chord | Remove Airfoil details Airfoil plotter |
(rg1495-il) RG 14 9.5% AIRFOIL | Rolf Girsberger RG 14 (9.5%) airfoil Max thickness 9.5% at 31% chord Max camber 1.6% at 36% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe679-il,rg1495-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe679-il | 50,000 | 9 | 5.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 50,000 | 5 | 25.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 100,000 | 9 | 42.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 100,000 | 5 | 41.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 200,000 | 9 | 58.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 200,000 | 5 | 54.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 500,000 | 9 | 76.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 500,000 | 5 | 72.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe679-il | 1,000,000 | 9 | 95.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe679-il | 1,000,000 | 5 | 88.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 50,000 | 9 | 32.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 50,000 | 5 | 33.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 100,000 | 9 | 48.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 100,000 | 5 | 46.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 200,000 | 9 | 63.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 200,000 | 5 | 57.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 500,000 | 9 | 82.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 500,000 | 5 | 71.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 1,000,000 | 9 | 89.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 1,000,000 | 5 | 85 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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