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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(goe677-il) GOE 677 (= M 6) AIRFOIL | Gottingen 677 (= M 6) airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(cast102-il) CAST 10-2/DOA 2 AIRFOIL | CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe677-il,cast102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe677-il | 50,000 | 9 | 29.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe677-il | 50,000 | 5 | 33 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe677-il | 100,000 | 9 | 49.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe677-il | 100,000 | 5 | 48.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe677-il | 200,000 | 9 | 66.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe677-il | 200,000 | 5 | 63.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe677-il | 500,000 | 9 | 87.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe677-il | 500,000 | 5 | 73.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe677-il | 1,000,000 | 9 | 94.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe677-il | 1,000,000 | 5 | 81.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 5 | 30.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 9 | 45.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 9 | 64 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 5 | 55.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 9 | 85.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 5 | 66.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 9 | 93.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 5 | 75.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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