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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(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 |
(e396-il) EPPLER 396 AIRFOIL | Eppler E396 human powered aircraft airfoil Max thickness 13.1% at 29.5% chord Max camber 5.4% at 52.1% chord | Remove Airfoil details Airfoil plotter |
(goe63-il) GOE 63 AIRFOIL | Gottingen 63 airfoil Max thickness 8.3% at 19.9% chord Max camber 6.7% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg15a111-il,e396-il,goe63-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
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 | |
e396-il | 50,000 | 9 | 25.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e396-il | 50,000 | 5 | 22.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e396-il | 100,000 | 9 | 54.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e396-il | 100,000 | 5 | 57.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e396-il | 200,000 | 9 | 89.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e396-il | 200,000 | 5 | 90.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e396-il | 500,000 | 9 | 135.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e396-il | 500,000 | 5 | 128.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e396-il | 1,000,000 | 9 | 169.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e396-il | 1,000,000 | 5 | 148 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe63-il | 50,000 | 9 | 30.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe63-il | 50,000 | 5 | 41.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe63-il | 100,000 | 9 | 61 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe63-il | 100,000 | 5 | 63.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe63-il | 200,000 | 9 | 86.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe63-il | 200,000 | 5 | 80.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe63-il | 500,000 | 9 | 110.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe63-il | 500,000 | 5 | 102.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe63-il | 1,000,000 | 9 | 128.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe63-il | 1,000,000 | 5 | 121.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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