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 | ||
(raf28-il) RAF 28 AIRFOIL | RAF-28 airfoil Max thickness 9.8% at 30% chord Max camber 1.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(raf48-il) RAF-48 AIRFOIL | RAF-48 airfoil Max thickness 15% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(e379-il) EPPLER 379 AIRFOIL | Eppler E379 ultralight airfoil Max thickness 2.2% at 5.8% chord Max camber 8% at 31.8% chord | Remove Airfoil details Airfoil plotter |
(df102-il) DF102 | David Fraser DF 102 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.4% at 43.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (raf28-il,raf48-il,e379-il,df102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf28-il | 50,000 | 9 | 35.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 50,000 | 5 | 35.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 9 | 52.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 5 | 50.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 9 | 69.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 5 | 64.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 9 | 90.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 5 | 79.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 9 | 103.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 5 | 83.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 50,000 | 9 | 7.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 50,000 | 5 | 25.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 9 | 45.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 5 | 49.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 9 | 68.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 9 | 97.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 9 | 121.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 5 | 108.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 50,000 | 9 | 23.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 50,000 | 5 | 40.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 100,000 | 9 | 74.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 100,000 | 5 | 66.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 200,000 | 9 | 117.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 200,000 | 5 | 91.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 500,000 | 9 | 128 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e379-il | 500,000 | 5 | 118.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e379-il | 1,000,000 | 0 | 135.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 50,000 | 9 | 32.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 50,000 | 5 | 32.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 100,000 | 9 | 49.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 100,000 | 5 | 45.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 200,000 | 9 | 64.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 200,000 | 5 | 56.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 500,000 | 9 | 82.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 500,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 1,000,000 | 9 | 93.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 1,000,000 | 5 | 93 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||