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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(rae102-il) RAE 102 AIRFOIL | RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe274-il) GOE 274 (DAIMLER V) AIRFOIL | Gottingen 274 (DAIMLER V) airfoil Max thickness 8.7% at 29.9% chord Max camber 4.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae102-il,goe274-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae102-il | 50,000 | 9 | 28.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae102-il | 50,000 | 5 | 27.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae102-il | 100,000 | 9 | 39.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae102-il | 100,000 | 5 | 36.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae102-il | 200,000 | 9 | 50.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae102-il | 200,000 | 5 | 41.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae102-il | 500,000 | 9 | 57.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae102-il | 500,000 | 5 | 54.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae102-il | 1,000,000 | 9 | 65.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae102-il | 1,000,000 | 5 | 68.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe274-il | 50,000 | 9 | 37.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe274-il | 50,000 | 5 | 40.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe274-il | 100,000 | 9 | 55.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe274-il | 100,000 | 5 | 57 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe274-il | 200,000 | 9 | 73.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe274-il | 200,000 | 5 | 73.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe274-il | 500,000 | 9 | 99 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe274-il | 500,000 | 5 | 92.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe274-il | 1,000,000 | 9 | 115.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe274-il | 1,000,000 | 5 | 105.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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