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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(npl9510-il) NPL 9510 AIRFOIL | NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord | Remove Airfoil details Airfoil plotter |
(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL | NASA/Langley RC-08(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord | Remove Airfoil details Airfoil plotter |
(r1080-il) RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL | Roncz 1080 Voyager inner aft wing airfoil Max thickness 18% at 40% chord Max camber 3.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(oaf117-il) OAF117 AIRFOIL | ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (npl9510-il,rc08n1-il,r1080-il,oaf117-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9510-il | 50,000 | 9 | 15.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 50,000 | 5 | 17 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 100,000 | 9 | 18.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 100,000 | 5 | 23.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 200,000 | 9 | 25.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 200,000 | 5 | 32.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 500,000 | 9 | 40.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 500,000 | 5 | 49.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 1,000,000 | 9 | 57.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 1,000,000 | 5 | 67.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 50,000 | 9 | 33.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 50,000 | 5 | 33.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 100,000 | 9 | 48.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 100,000 | 5 | 45.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 200,000 | 9 | 63.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 200,000 | 5 | 56.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 500,000 | 9 | 81.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 500,000 | 5 | 67.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 1,000,000 | 9 | 91.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 1,000,000 | 5 | 76.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 50,000 | 9 | 5.8 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 50,000 | 5 | 13.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 100,000 | 9 | 28 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 100,000 | 5 | 22.9 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 200,000 | 9 | 55.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 200,000 | 5 | 55.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 500,000 | 9 | 106.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 500,000 | 5 | 102.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 1,000,000 | 9 | 139.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 1,000,000 | 5 | 127 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 9 | 28.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 9 | 46.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 5 | 49.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 9 | 64.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 5 | 63 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 9 | 84.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 5 | 78.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 9 | 96.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 5 | 89.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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