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 | ||
(cr001sm-il) cr001sm | Cody Robertson CR 001 R/C hand-launch low Reynolds number airfoil (smoothed) Max thickness 7.3% at 27.1% chord Max camber 4.1% at 45.4% chord | Remove Airfoil details Airfoil plotter |
(goe399-il) GOE 399 AIRFOIL | Gottingen 399 airfoil Max thickness 6.9% at 29.9% chord Max camber 4.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe285-il) GOE 285 AIRFOIL | Gottingen 285 airfoil Max thickness 11.7% at 30% chord Max camber 3.7% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (cr001sm-il,goe399-il,goe285-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cr001sm-il | 50,000 | 9 | 41.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 50,000 | 5 | 44.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 100,000 | 9 | 64.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 100,000 | 5 | 64.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 200,000 | 9 | 89.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 200,000 | 5 | 83.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 500,000 | 9 | 120.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 500,000 | 5 | 105.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 1,000,000 | 9 | 139.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 1,000,000 | 5 | 119.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 50,000 | 9 | 40.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 50,000 | 5 | 41.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 100,000 | 9 | 59.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 100,000 | 5 | 60.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 200,000 | 9 | 79.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 200,000 | 5 | 76.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 500,000 | 9 | 104.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 500,000 | 5 | 98.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 1,000,000 | 9 | 124.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 1,000,000 | 5 | 112.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 50,000 | 9 | 26.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 50,000 | 5 | 34.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 100,000 | 9 | 47.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 100,000 | 5 | 50.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 200,000 | 9 | 65.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 200,000 | 5 | 65.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 500,000 | 9 | 89.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 500,000 | 5 | 87 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 1,000,000 | 9 | 109.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 1,000,000 | 5 | 103.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||