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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(stcyr24-il) St. CYR 24 (Bartel 35-IIIC) | St. CYR 24 (Bartel 35-IIIC) airfoil Max thickness 12.4% at 30% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(rc410-il) NASA RC(4)-10 AIRFOIL | NASA/Langley RC(4)-10 rotorcraft airfoil Max thickness 10% at 37.8% chord Max camber 2.1% at 30.3% chord | Remove Airfoil details Airfoil plotter |
(npl9660-il) NPL 9660 AIRFOIL | NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
(e395-il) EPPLER 395 AIRFOIL | Eppler E395 human e664ered aircraft airfoil Max thickness 12.3% at 29.5% chord Max camber 5.2% at 52.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (stcyr24-il,rc410-il,npl9660-il,e395-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| stcyr24-il | 50,000 | 9 | 29.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 50,000 | 5 | 31.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 100,000 | 9 | 56.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 100,000 | 5 | 53.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 200,000 | 9 | 82.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 200,000 | 5 | 74.2 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 500,000 | 9 | 116.5 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 500,000 | 5 | 89.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr24-il | 1,000,000 | 9 | 126.9 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr24-il | 1,000,000 | 5 | 95.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc410-il | 50,000 | 9 | 28.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc410-il | 50,000 | 5 | 27.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc410-il | 100,000 | 9 | 39.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc410-il | 100,000 | 5 | 37.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc410-il | 200,000 | 9 | 47.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc410-il | 200,000 | 5 | 51.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc410-il | 500,000 | 9 | 69.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc410-il | 500,000 | 5 | 73.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc410-il | 1,000,000 | 9 | 91.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc410-il | 1,000,000 | 5 | 92.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 50,000 | 9 | 28 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 50,000 | 5 | 30.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 9 | 41.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 5 | 41.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 9 | 54.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 5 | 51.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 9 | 69.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 5 | 66.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 9 | 81.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 5 | 75.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 50,000 | 9 | 31 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 50,000 | 5 | 28.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 100,000 | 9 | 59.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 100,000 | 5 | 61.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 200,000 | 9 | 92.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 200,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 500,000 | 9 | 136.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 500,000 | 5 | 128.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 9 | 169.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 5 | 144.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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