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 | ||
(ah82150a-il) AH 82-150 A | Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(sd7037-il) SD7037-092-88 | Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ah82150a-il,sd7037-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah82150a-il | 50,000 | 9 | 17.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 50,000 | 5 | 20.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 5 | 41.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 9 | 72.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 5 | 73.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 9 | 108.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 5 | 107.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 9 | 137.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 5 | 129.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 50,000 | 9 | 34.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 50,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 100,000 | 9 | 55.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 100,000 | 5 | 55.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 200,000 | 5 | 70.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 500,000 | 9 | 99.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 500,000 | 5 | 90.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 1,000,000 | 9 | 116 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 1,000,000 | 5 | 104.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||