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 | ||
(us1000root-il) US1000ROOT | Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(usa27m2-il) USA 27 mod. AIRFOIL | USA-27MOD airfoil Max thickness 13.3% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (us1000root-il,usa27m2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| us1000root-il | 50,000 | 9 | 19 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 50,000 | 5 | 24.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 9 | 38.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 100,000 | 5 | 38.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 9 | 49.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 200,000 | 5 | 44.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 9 | 49.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 500,000 | 5 | 43.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 9 | 52.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| us1000root-il | 1,000,000 | 5 | 45.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 50,000 | 9 | 17.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 50,000 | 5 | 32.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 100,000 | 9 | 47.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 100,000 | 5 | 48.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 200,000 | 9 | 64.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 200,000 | 5 | 62.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 500,000 | 9 | 86.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 500,000 | 5 | 85 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 1,000,000 | 9 | 110 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 1,000,000 | 5 | 102.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||