Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL | Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
(goe344-il) GOE 344 (PFALZ 71) AIRFOIL | Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe507-il) GOE 507 AIRFOIL | Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (v43015-il,goe344-il,goe507-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 50,000 | 9 | 32.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 50,000 | 5 | 34.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 100,000 | 9 | 45.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 100,000 | 5 | 47.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 200,000 | 9 | 60.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 200,000 | 5 | 60.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 500,000 | 9 | 80.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 500,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 1,000,000 | 9 | 95.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 1,000,000 | 5 | 89 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 50,000 | 9 | 37.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 50,000 | 5 | 38 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 100,000 | 9 | 55.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 100,000 | 5 | 53.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 200,000 | 9 | 73.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 200,000 | 5 | 67.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 500,000 | 9 | 95.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 500,000 | 5 | 82 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe507-il | 1,000,000 | 9 | 106.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe507-il | 1,000,000 | 5 | 89.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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