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 | ||
(giiih-il) GIII BL207 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (giiih-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiih-il | 50,000 | 9 | 33.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 50,000 | 5 | 32.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 100,000 | 9 | 47.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 100,000 | 5 | 44.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 200,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 200,000 | 5 | 55.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 500,000 | 9 | 78.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 500,000 | 5 | 60.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiih-il | 1,000,000 | 9 | 82.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiih-il | 1,000,000 | 5 | 74.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||