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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(sd7034-il) SD7034 | Selig/Donovan SD7034 low Reynolds number airfoil Max thickness 10.5% at 26% chord Max camber 3.6% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(sc20412-il) NASA SC(2)-0412 AIRFOIL | NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord | Remove Airfoil details Airfoil plotter |
(sc20712-il) NASA SC(2)-0712 AIRFOIL | NASA SC(2)-0712 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 2.2% at 81% chord | Remove Airfoil details Airfoil plotter |
(goe116-il) GOE 116 (MVA MK.3) AIRFOIL | Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord Max camber 4.1% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7034-il,sc20412-il,sc20712-il,goe116-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7034-il | 50,000 | 9 | 27.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 50,000 | 5 | 37.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 100,000 | 9 | 54.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 100,000 | 5 | 57.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 200,000 | 9 | 77.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 200,000 | 5 | 76.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 500,000 | 5 | 99.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 1,000,000 | 9 | 128.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 1,000,000 | 5 | 116.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20412-il | 50,000 | 9 | 24.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20412-il | 50,000 | 5 | 21.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20412-il | 100,000 | 9 | 26.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20412-il | 100,000 | 5 | 30.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20412-il | 200,000 | 9 | 35.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20412-il | 200,000 | 5 | 43 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20412-il | 500,000 | 9 | 56.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20412-il | 500,000 | 5 | 63 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20412-il | 1,000,000 | 9 | 75.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20412-il | 1,000,000 | 5 | 78.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 50,000 | 9 | 24.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 50,000 | 5 | 23.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 100,000 | 9 | 32 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 100,000 | 5 | 33.4 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 200,000 | 9 | 43.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 200,000 | 5 | 47.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 500,000 | 9 | 70.6 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 500,000 | 5 | 64.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 1,000,000 | 9 | 85.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 1,000,000 | 5 | 80.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 50,000 | 9 | 29.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 50,000 | 5 | 37.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 9 | 58 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 5 | 56.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 9 | 78.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 5 | 76.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 9 | 106.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 5 | 81.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 9 | 100.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 5 | 91.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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