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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(rg149-il) RG 14 9% AIRFOIL | Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% chord | Remove Airfoil details Airfoil plotter |
(rg15a111-il) RG 15A-1.8/11.0 AIRFOIL | Rolf Girsberger RG 15A-1.8/11.0 airfoil Max thickness 11% at 30.2% chord Max camber 1.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe423-il) GOE 423 AIRFOIL | Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord Max camber 5.1% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe600-il) GOE 600 AIRFOIL | Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord Max camber 1.9% at 49.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg149-il,rg15a111-il,goe423-il,goe600-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg149-il | 50,000 | 9 | 33.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 50,000 | 5 | 34.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 9 | 48.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 5 | 46.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 9 | 63.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 5 | 57.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 9 | 81.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 5 | 70.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 9 | 90 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 5 | 84.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 9 | 32.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 5 | 35.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 9 | 50 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 9 | 66.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 5 | 62.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 9 | 87.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 5 | 79.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 9 | 101.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 5 | 90 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 50,000 | 9 | 4.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 50,000 | 5 | 14.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 9 | 22.8 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 5 | 40.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 9 | 69.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 5 | 70.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 9 | 105.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 5 | 101.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 9 | 133.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 5 | 124.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 9 | 32.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 5 | 33.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 5 | 49.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 9 | 69.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 5 | 62.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 9 | 91.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 9 | 99.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 5 | 86 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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