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 | ||
(curtisc72-il) Curtis C-72 | Curtis C-72 airfoil Max thickness 11.7% at 30% chord Max camber 3.8% at 50% chord | Remove Airfoil details Airfoil plotter |
(e203-il) E203 (13.64%) | Eppler E203 low Reynolds number airfoil Max thickness 13.6% at 30.7% chord Max camber 2.3% at 54.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (curtisc72-il,e203-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| curtisc72-il | 50,000 | 9 | 29.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 50,000 | 5 | 37.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 100,000 | 9 | 54.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 100,000 | 5 | 56.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 200,000 | 9 | 76.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 200,000 | 5 | 73.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 500,000 | 9 | 103.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 500,000 | 5 | 95.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| curtisc72-il | 1,000,000 | 9 | 121 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| curtisc72-il | 1,000,000 | 5 | 114.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 50,000 | 9 | 32 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 50,000 | 5 | 31.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 100,000 | 9 | 54.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 100,000 | 5 | 55 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 200,000 | 9 | 78.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 200,000 | 5 | 75.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 500,000 | 9 | 109.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 500,000 | 5 | 101.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e203-il | 1,000,000 | 9 | 132.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e203-il | 1,000,000 | 5 | 108.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||