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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(sd7032-il) SD7032-099-88 | Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord | Remove Airfoil details Airfoil plotter |
(goe277-il) GOE 277 (DAIMLER VIII) AIRFOIL | Gottingen 277 (DAIMLER VIII) airfoil Max thickness 8.3% at 29.9% chord Max camber 4.4% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe309-il) GOE 309 (MVA H.41) AIRFOIL | Gottingen 309 (MVA H.41) airfoil Max thickness 8.4% at 30% chord Max camber 4.7% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7032-il,goe277-il,goe309-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7032-il | 50,000 | 9 | 31.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7032-il | 50,000 | 5 | 39.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7032-il | 100,000 | 9 | 56.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7032-il | 100,000 | 5 | 58 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7032-il | 200,000 | 9 | 77.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7032-il | 200,000 | 5 | 75.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7032-il | 500,000 | 9 | 105.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7032-il | 500,000 | 5 | 97.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7032-il | 1,000,000 | 9 | 125.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7032-il | 1,000,000 | 5 | 114.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe277-il | 50,000 | 9 | 34 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe277-il | 50,000 | 5 | 38.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe277-il | 100,000 | 9 | 54.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe277-il | 100,000 | 5 | 55.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe277-il | 200,000 | 9 | 73.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe277-il | 200,000 | 5 | 73.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe277-il | 500,000 | 9 | 100.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe277-il | 500,000 | 5 | 98.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe277-il | 1,000,000 | 9 | 122.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe277-il | 1,000,000 | 5 | 118.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe309-il | 50,000 | 9 | 34.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe309-il | 50,000 | 5 | 37.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe309-il | 100,000 | 9 | 54.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe309-il | 100,000 | 5 | 55.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe309-il | 200,000 | 9 | 73.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe309-il | 200,000 | 5 | 71.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe309-il | 500,000 | 9 | 97 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe309-il | 500,000 | 5 | 90.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe309-il | 1,000,000 | 9 | 113.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe309-il | 1,000,000 | 5 | 101.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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