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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(goe507-il) GOE 507 AIRFOIL | Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(dbln526-il) SIKORSKY DBLN-526 AIRFOIL | Sikorsky DBLN-526 double ended rotorcraft airfoil Max thickness 26% at 50% chord Max camber 4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe507-il,dbln526-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe507-il | 50,000 | 9 | 37.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 50,000 | 5 | 38 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 100,000 | 9 | 55.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 100,000 | 5 | 53.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 200,000 | 9 | 73.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 200,000 | 5 | 67.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 500,000 | 9 | 95.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 500,000 | 5 | 82 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 1,000,000 | 9 | 106.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 1,000,000 | 5 | 89.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 50,000 | 9 | 4.9 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 50,000 | 5 | 10.8 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 100,000 | 9 | 20 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 100,000 | 5 | 19.7 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 200,000 | 9 | 35 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 200,000 | 5 | 31 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 500,000 | 9 | 47.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 500,000 | 5 | 41.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dbln526-il | 1,000,000 | 9 | 53.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dbln526-il | 1,000,000 | 5 | 34.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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