Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(rc10n1-il) NASA/LANGLEY RC-10(N)1 AIRFOIL | NASA/Langley RC-10(N)1 rotorcraft airfoil Max thickness 10% at 37.6% chord Max camber 1.5% at 25% chord | Remove Airfoil details Airfoil plotter |
(rhodesg34-il) Rhode St. Genese 34 | Rhode St. Genese 34 airfoil Max thickness 14.1% at 30% chord Max camber 4.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(rhodesg36-il) Rhode St. Genese 36 | Rhode St. Genese 36 airfoil Max thickness 16.2% at 30% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(rc510-il) NASA RC(5)-10 AIRFOIL | NASA/Langley RC(5)-10 rotorcraft airfoil Max thickness 10% at 40.1% chord Max camber 2.2% at 25.3% 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 |
Drawing Options
Polars for (rc10n1-il,rhodesg34-il,rhodesg36-il,rc510-il,rc410-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc10n1-il | 50,000 | 9 | 33.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 50,000 | 5 | 33.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 100,000 | 9 | 49 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 100,000 | 5 | 46.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 200,000 | 9 | 65.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 200,000 | 5 | 59.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 500,000 | 9 | 84.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 500,000 | 5 | 70.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 1,000,000 | 9 | 94.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 1,000,000 | 5 | 78.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg34-il | 50,000 | 9 | 20.4 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg34-il | 50,000 | 5 | 30.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg34-il | 100,000 | 9 | 43.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg34-il | 100,000 | 5 | 45.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg34-il | 200,000 | 9 | 58.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg34-il | 200,000 | 5 | 59.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg34-il | 500,000 | 9 | 81.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg34-il | 500,000 | 5 | 81.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg34-il | 1,000,000 | 9 | 107.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg34-il | 1,000,000 | 5 | 103.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg36-il | 50,000 | 9 | 13.3 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg36-il | 50,000 | 5 | 27.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg36-il | 100,000 | 9 | 42.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg36-il | 100,000 | 5 | 41.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg36-il | 200,000 | 9 | 54 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg36-il | 200,000 | 5 | 52.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg36-il | 500,000 | 9 | 70.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg36-il | 500,000 | 5 | 70.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg36-il | 1,000,000 | 9 | 91 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg36-il | 1,000,000 | 5 | 91.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 9 | 31.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 5 | 32.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 9 | 46.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 5 | 43.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 9 | 60.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 5 | 54.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 9 | 76.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 5 | 75.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 9 | 94.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 5 | 92.4 at α=8.25° | 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 | |
| Reynolds number calculator | |||||||