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 | ||
(rg149-il) RG 14 9% AIRFOIL | Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% 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 |
(s102s-il) SOMERS S102 AIRFOIL (SHARP) | Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord | Remove Airfoil details Airfoil plotter |
(rg15a111-il) RG 15A-1.8/11.0 AIRFOIL | Rolf Girsberger RG 15A-1.8/11.0 airfoil Max thickness 11% at 30.2% chord Max camber 1.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (rg149-il,rc08n1-il,s102s-il,rg15a111-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg149-il | 50,000 | 9 | 33.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 50,000 | 5 | 34.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 9 | 48.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 5 | 46.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 9 | 63.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 5 | 57.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 9 | 81.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 5 | 70.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 9 | 90 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 5 | 84.2 at α=6.5° | 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 | |
| s102s-il | 50,000 | 9 | 30.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 50,000 | 5 | 26.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 100,000 | 9 | 40.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 100,000 | 5 | 42.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 200,000 | 9 | 59.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 200,000 | 5 | 57 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 500,000 | 9 | 82.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 500,000 | 5 | 69.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 1,000,000 | 9 | 95.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 1,000,000 | 5 | 82.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 9 | 32.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 5 | 35.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 9 | 50 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 9 | 66.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 5 | 62.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 9 | 87.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 5 | 79.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 9 | 101.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 5 | 90 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||