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 | ||
(ah21-7-il) AH21 7% version (Andrew Hollom) | Andrew Hollom AH 21 airfoil (7% version) Max thickness 9% at 34.9% chord Max camber 2.3% at 54.8% chord | Remove Airfoil details Airfoil plotter |
(ag46c03-il) AG46c -03f | Drela AG46c -03f airfoil Max thickness 6% at 23.3% chord Max camber 1.9% at 37.3% chord | Remove Airfoil details Airfoil plotter |
(ah80129-il) AH 80-129 | Althaus AH 80-129 airfoil Max thickness 12.9% at 40.2% chord Max camber 4.1% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(ah6407-il) AH-6-40-7 AIRFOIL | Althaus AH 6-407 airfoil Max thickness 6.9% at 20% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ah21-7-il,ag46c03-il,ah80129-il,ah6407-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah21-7-il | 50,000 | 9 | 35.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 5 | 51.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 9 | 78.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 5 | 69.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 9 | 111.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 5 | 82.9 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 5 | 84.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 50,000 | 9 | 30.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 50,000 | 5 | 33.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 100,000 | 9 | 44.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 100,000 | 5 | 44.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 200,000 | 9 | 58.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 200,000 | 5 | 55.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 500,000 | 9 | 74.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 500,000 | 5 | 72.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 1,000,000 | 9 | 88.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 1,000,000 | 5 | 86 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 50,000 | 9 | 18.2 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 50,000 | 5 | 19 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 100,000 | 9 | 37.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 100,000 | 5 | 39.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 200,000 | 9 | 79 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 200,000 | 5 | 78.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 500,000 | 9 | 124.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 500,000 | 5 | 121.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 1,000,000 | 9 | 152.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 1,000,000 | 5 | 143.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 50,000 | 9 | 41.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 50,000 | 5 | 46.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 9 | 67.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 5 | 67.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 9 | 91.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 5 | 85.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 5 | 104 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 9 | 131.3 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 5 | 121.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||