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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(raf25-il) RAF 25 AIRFOIL | RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord | Remove Airfoil details Airfoil plotter |
(goe147-il) GOE 147 (MVA H.6) AIRFOIL | Gottingen 147 (MVA H.6) airfoil Max thickness 7.5% at 14.9% chord Max camber 3.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf25-il,goe147-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
raf25-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf25-il | 50,000 | 5 | 30.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf25-il | 100,000 | 9 | 43.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf25-il | 100,000 | 5 | 40.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf25-il | 200,000 | 9 | 56.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf25-il | 200,000 | 5 | 47.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf25-il | 500,000 | 9 | 68.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf25-il | 500,000 | 5 | 55.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf25-il | 1,000,000 | 9 | 72.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf25-il | 1,000,000 | 5 | 68.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe147-il | 50,000 | 9 | 29.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe147-il | 50,000 | 5 | 36.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe147-il | 100,000 | 9 | 48.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe147-il | 100,000 | 5 | 49.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe147-il | 200,000 | 9 | 64.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe147-il | 200,000 | 5 | 66.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe147-il | 500,000 | 9 | 86.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe147-il | 500,000 | 5 | 86.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe147-il | 1,000,000 | 9 | 102.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe147-il | 1,000,000 | 5 | 101.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |