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 | ||
(sd7090-il) SD7090 (10%) | Selig/Donovan SD7090 low Reynolds number airfoil Max thickness 10% at 29.3% chord Max camber 1.5% at 43.6% chord | Remove Airfoil details Airfoil plotter |
(rg14a147-il) RG 14A-1.4/7.0 AIRFOIL | Rolf Girsberger RG 14A-1.4/7.0 airfoil Max thickness 7% at 29.7% chord Max camber 1.4% at 34.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sd7090-il,rg14a147-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7090-il | 50,000 | 9 | 30.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7090-il | 50,000 | 5 | 34.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7090-il | 100,000 | 9 | 47.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7090-il | 100,000 | 5 | 47.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7090-il | 200,000 | 9 | 62.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7090-il | 200,000 | 5 | 60.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7090-il | 500,000 | 9 | 83.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7090-il | 500,000 | 5 | 78.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7090-il | 1,000,000 | 9 | 99 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7090-il | 1,000,000 | 5 | 92.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 50,000 | 9 | 33.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 50,000 | 5 | 34.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 100,000 | 9 | 48.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 100,000 | 5 | 45.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 200,000 | 9 | 62.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 200,000 | 5 | 56.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 500,000 | 9 | 78.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 500,000 | 5 | 67.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14a147-il | 1,000,000 | 9 | 88 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14a147-il | 1,000,000 | 5 | 76.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||