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 | ||
(ag36-il) AG36 | Drela AG36 airfoil Max thickness 8.2% at 27.9% chord Max camber 2.3% at 37% chord | Remove Airfoil details Airfoil plotter |
(mh64-il) MH 64 8.59% | Martin Hepperle MH 64 for flying wings Max thickness 8.6% at 26.9% chord Max camber 1.4% at 41.8% chord | Remove Airfoil details Airfoil plotter |
(e638-il) EPPLER 638 AIRFOIL | Eppler E638 airfoil Max thickness 12.4% at 28.5% chord Max camber 4.4% at 24.5% chord | Remove Airfoil details Airfoil plotter |
(mh44-il) MH 44 9.66% | Martin Hepperle MH 44 for flying wings Max thickness 9.6% at 27.1% chord Max camber 1.5% at 36.9% chord | Remove Airfoil details Airfoil plotter |
(e657-il) EPPLER 657 AIRFOIL | Eppler E657 sailplane airfoil Max thickness 15.6% at 37% chord Max camber 4.6% at 47.6% chord | Remove Airfoil details Airfoil plotter |
(e520-il) EPPLER 520 AIRFOIL | Eppler E520 tailplane airfoil Max thickness 15% at 36.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ag36-il,mh64-il,e638-il,mh44-il,e657-il,e520-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag36-il | 50,000 | 9 | 32.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 50,000 | 5 | 36.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 100,000 | 9 | 50.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 100,000 | 5 | 51 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 200,000 | 9 | 67.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 200,000 | 5 | 64.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 500,000 | 9 | 88.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 500,000 | 5 | 81 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag36-il | 1,000,000 | 9 | 103 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag36-il | 1,000,000 | 5 | 93 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 50,000 | 9 | 29.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 50,000 | 5 | 33.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 100,000 | 9 | 44.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 100,000 | 5 | 45.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 200,000 | 9 | 59.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 200,000 | 5 | 57 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 500,000 | 9 | 78 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 500,000 | 5 | 72.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 1,000,000 | 9 | 90.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 1,000,000 | 5 | 84 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 50,000 | 9 | 14.4 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 50,000 | 5 | 25.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 100,000 | 9 | 32.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 100,000 | 5 | 45.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 200,000 | 9 | 62.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 200,000 | 5 | 68.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 500,000 | 9 | 99.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 500,000 | 5 | 100.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 1,000,000 | 9 | 129.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 1,000,000 | 5 | 126 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 50,000 | 9 | 29.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 50,000 | 5 | 32.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 100,000 | 9 | 44.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 100,000 | 5 | 45.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 200,000 | 9 | 60.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 200,000 | 5 | 58.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 500,000 | 9 | 80.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 500,000 | 5 | 74.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh44-il | 1,000,000 | 9 | 94.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh44-il | 1,000,000 | 5 | 87.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 50,000 | 9 | 7.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 50,000 | 5 | 18.7 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 100,000 | 9 | 41.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 100,000 | 5 | 35.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 200,000 | 9 | 72 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 200,000 | 5 | 70.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 500,000 | 9 | 126.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 500,000 | 5 | 117.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 1,000,000 | 9 | 160.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 1,000,000 | 5 | 145 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 50,000 | 9 | 28.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 50,000 | 5 | 27.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 100,000 | 9 | 41.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 100,000 | 5 | 35.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 200,000 | 9 | 47.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 200,000 | 5 | 45.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 500,000 | 9 | 62.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 500,000 | 5 | 57.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 1,000,000 | 9 | 71.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 1,000,000 | 5 | 67.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||