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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(npl9615-il) NPL 9615 AIRFOIL | NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
(goe587-il) GOE 587 AIRFOIL | Gottingen 587 airfoil Max thickness 5.8% at 40% chord Max camber 3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe287-il) GOE 287 AIRFOIL | Gottingen 287 airfoil Max thickness 8.9% at 29.9% chord Max camber 4.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (npl9615-il,goe587-il,goe287-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9615-il | 50,000 | 9 | 29 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 5 | 30.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 9 | 43.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 5 | 42.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 9 | 56.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 9 | 70.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 5 | 68.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 9 | 84.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 5 | 77.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 50,000 | 9 | 36.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 50,000 | 5 | 37 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 100,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 100,000 | 5 | 50.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 200,000 | 9 | 63.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 200,000 | 5 | 62.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 500,000 | 9 | 77.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 500,000 | 5 | 70.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe587-il | 1,000,000 | 9 | 77.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe587-il | 1,000,000 | 5 | 77.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 50,000 | 9 | 36.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 50,000 | 5 | 38 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 100,000 | 9 | 58.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 100,000 | 5 | 59.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 200,000 | 9 | 80 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 200,000 | 5 | 77.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 500,000 | 9 | 106.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 500,000 | 5 | 94.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 1,000,000 | 9 | 123 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 1,000,000 | 5 | 106.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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