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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(goe767-il) GOE 767 AIRFOIL | Gottingen 767 airfoil Max thickness 12% at 20% chord Max camber 1.5% at 20% chord | Remove Airfoil details Airfoil plotter |
(goe79-il) GOE 79 (PFALZ 11) AIRFOIL | Gottingen 79 (Pfalz 11) airfoil Max thickness 6.2% at 14.9% chord Max camber 6% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL | Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe81-il) GOE 81 AIRFOIL | Gottingen 81 airfoil Max thickness 7.4% at 29.9% chord Max camber 6.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe767-il,goe79-il,hh02-il,goe81-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe767-il | 50,000 | 9 | 15.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 50,000 | 5 | 23.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 100,000 | 9 | 30.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 100,000 | 5 | 38.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 200,000 | 9 | 49.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 200,000 | 5 | 54.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 500,000 | 9 | 76 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 500,000 | 5 | 74.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 1,000,000 | 9 | 93.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 1,000,000 | 5 | 91.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 50,000 | 9 | 59.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 50,000 | 5 | 42.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 100,000 | 9 | 57.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 100,000 | 5 | 59.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 200,000 | 9 | 75.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 200,000 | 5 | 75.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 500,000 | 9 | 102.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 500,000 | 5 | 97.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 1,000,000 | 9 | 120.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 1,000,000 | 5 | 103.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 50,000 | 9 | 30.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 50,000 | 5 | 33.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 100,000 | 9 | 46.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 100,000 | 5 | 45.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 200,000 | 9 | 60.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 200,000 | 5 | 56.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 500,000 | 9 | 76.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 500,000 | 5 | 72.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 1,000,000 | 9 | 89.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 1,000,000 | 5 | 84.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 50,000 | 9 | 31.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 50,000 | 5 | 42.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 100,000 | 9 | 61.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 100,000 | 5 | 65.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 200,000 | 9 | 89.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 200,000 | 5 | 83.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 500,000 | 9 | 114.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 500,000 | 5 | 102.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 1,000,000 | 9 | 133.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 1,000,000 | 5 | 104.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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