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 | ||
(naca0024-il) NACA 0024 | NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe13k-il) GOE 13K AIRFOIL | Gottingen 13K airfoil Max thickness 14.8% at 50% chord Max camber 5.5% at 60% chord | Remove Airfoil details Airfoil plotter |
(jn153-il) JN-153 AIRFOIL | Narramore JN153 airfoil Max thickness 17.6% at 28.2% chord Max camber 8.4% at 38.1% chord | Remove Airfoil details Airfoil plotter |
(goe746-il) GOE 746 AIRFOIL | Gottingen 746 airfoil Max thickness 9.8% at 30% chord Max camber 5% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe280-il) GOE 280 (DAIMLER XI) AIRFOIL | Gottingen 280 (DAIMLER XI) airfoil Max thickness 7.9% at 30% chord Max camber 4.5% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca0024-il,goe13k-il,jn153-il,goe746-il,goe280-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0024-il | 50,000 | 9 | 15.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 50,000 | 5 | 21.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 9 | 34.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 100,000 | 5 | 30.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 9 | 43 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 200,000 | 5 | 37 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 9 | 52.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 500,000 | 5 | 50.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 9 | 68.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0024-il | 1,000,000 | 5 | 64.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 50,000 | 9 | 25.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 50,000 | 5 | 20.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 100,000 | 9 | 34.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 100,000 | 5 | 30.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 200,000 | 9 | 45.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 200,000 | 5 | 42.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 500,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 500,000 | 5 | 85.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 1,000,000 | 9 | 129 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 1,000,000 | 5 | 93.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 50,000 | 9 | 4.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 50,000 | 5 | 6.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 100,000 | 9 | 5.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 100,000 | 5 | 18.1 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 200,000 | 9 | 16.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 200,000 | 5 | 44.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 500,000 | 9 | 98.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 500,000 | 5 | 112.6 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 1,000,000 | 9 | 163.3 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 1,000,000 | 5 | 165.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 50,000 | 9 | 7.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 50,000 | 5 | 20.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 100,000 | 9 | 46.3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 100,000 | 5 | 49.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 200,000 | 9 | 73.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 200,000 | 5 | 73.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 500,000 | 9 | 106.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 500,000 | 5 | 102.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 1,000,000 | 9 | 129.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 1,000,000 | 5 | 118.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 50,000 | 9 | 37.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 50,000 | 5 | 41.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 9 | 55.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 5 | 56.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 9 | 72.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 5 | 70.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 9 | 91.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 5 | 79.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 9 | 98.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 5 | 87.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||