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 | ||
(goe184-il) GOE 184 (MVA H.29) AIRFOIL | Gottingen 184 (MVA H.29) airfoil Max thickness 8.3% at 19.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe16k-il) GOE 16K AIRFOIL | Gottingen 16K airfoil Max thickness 18.2% at 50% chord Max camber 4.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe15k-il) GOE 15K AIRFOIL | Gottingen 15K airfoil Max thickness 15% at 50% chord Max camber 3.4% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe184-il,goe16k-il,goe15k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe184-il | 50,000 | 9 | 34 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 50,000 | 5 | 39.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 100,000 | 9 | 57.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 100,000 | 5 | 60.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 200,000 | 9 | 79.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 200,000 | 5 | 79.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 500,000 | 9 | 107.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 500,000 | 5 | 102.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 1,000,000 | 9 | 127.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 1,000,000 | 5 | 111.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 50,000 | 9 | 21.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 50,000 | 5 | 16.6 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 9 | 26.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 100,000 | 5 | 23.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 200,000 | 9 | 35.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 9 | 69.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 500,000 | 5 | 50.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 9 | 80.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe16k-il | 1,000,000 | 5 | 70.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15k-il | 50,000 | 9 | 23.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15k-il | 50,000 | 5 | 20.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15k-il | 100,000 | 9 | 32.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15k-il | 100,000 | 5 | 30.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15k-il | 200,000 | 9 | 49.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15k-il | 200,000 | 5 | 49.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15k-il | 500,000 | 9 | 92.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15k-il | 500,000 | 5 | 67.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15k-il | 1,000,000 | 9 | 92.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15k-il | 1,000,000 | 5 | 83.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||