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 | ||
(goe09k-il) GOE 9K AIRFOIL | Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord | Remove Airfoil details Airfoil plotter |
(ag45ct02r-il) AG45ct -02f | Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord Max camber 1.8% at 33.1% chord | Remove Airfoil details Airfoil plotter |
(ag47c03-il) AG47c -03f | Drela AG47c -03f airfoil Max thickness 5.1% at 22.4% chord Max camber 1.3% at 33.4% chord | Remove Airfoil details Airfoil plotter |
(giiia-il) GIII BL0 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 11% at 39.7% chord Max camber 0.7% at 14.7% 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 |
Drawing Options
Polars for (goe09k-il,ag45ct02r-il,ag47c03-il,giiia-il,ag46c03-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe09k-il | 50,000 | 9 | 20.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 50,000 | 5 | 18.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 100,000 | 9 | 23.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 100,000 | 5 | 23.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 200,000 | 9 | 29.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 200,000 | 5 | 29.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 500,000 | 9 | 79.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 500,000 | 5 | 60.5 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 1,000,000 | 9 | 77.7 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 1,000,000 | 5 | 63.4 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 50,000 | 9 | 30.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 50,000 | 5 | 34.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 9 | 45.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 5 | 46.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 9 | 60.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 5 | 59.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 9 | 80.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 5 | 76.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 9 | 94.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 5 | 89.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 50,000 | 9 | 30.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 50,000 | 5 | 30.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 100,000 | 9 | 42.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 100,000 | 5 | 39.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 200,000 | 9 | 53 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 200,000 | 5 | 49.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 500,000 | 9 | 65.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 500,000 | 5 | 66.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47c03-il | 1,000,000 | 9 | 80.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47c03-il | 1,000,000 | 5 | 80.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 50,000 | 9 | 26.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 50,000 | 5 | 27.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 100,000 | 9 | 38.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 100,000 | 5 | 38.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 200,000 | 9 | 49.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 200,000 | 5 | 51.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 500,000 | 9 | 69.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 500,000 | 5 | 62.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiia-il | 1,000,000 | 9 | 77.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiia-il | 1,000,000 | 5 | 72 at α=6.5° | 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 | |
| Reynolds number calculator | |||||||