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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(goe765-il) Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 | Used on the Me163 Komet Max thickness 14.4% at 30% chord Max camber 1.9% at 25.9% chord | Remove Airfoil details Airfoil plotter |
(clarkw-il) CLARK W AIRFOIL | CLARK W airfoil Max thickness 11.2% at 30% chord Max camber 3.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe600-il) GOE 600 AIRFOIL | Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord Max camber 1.9% at 49.4% chord | Remove Airfoil details Airfoil plotter |
(arad13-il) ARA-D 13% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe633-il) GOE 633 AIRFOIL | Gottingen 633 airfoil Max thickness 13.8% at 19.7% chord Max camber 4% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(k1-il) NYU/GRUMMAN K-1 AIRFOIL | NYU/Grumman K-1 transonic airfoil (GAC .75-.63-11.6) Max thickness 11.6% at 33% chord Max camber 1.9% at 75% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe765-il,clarkw-il,goe600-il,arad13-il,goe633-il,k1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe765-il | 50,000 | 9 | 15.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 50,000 | 5 | 28.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 9 | 41.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 5 | 44.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 9 | 59.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 5 | 58.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 9 | 80.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 5 | 68.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 9 | 85.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 5 | 79.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 50,000 | 9 | 32.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 50,000 | 5 | 36.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 100,000 | 9 | 53.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 200,000 | 9 | 73.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 200,000 | 5 | 69.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 500,000 | 9 | 98.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 500,000 | 5 | 91.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 1,000,000 | 9 | 116.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 1,000,000 | 5 | 107.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 9 | 32.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 5 | 33.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 5 | 49.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 9 | 69.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 5 | 62.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 9 | 91.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 9 | 99.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 5 | 86 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 50,000 | 9 | 25.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 50,000 | 5 | 31.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 100,000 | 9 | 41.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 100,000 | 5 | 44.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 200,000 | 9 | 56.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 200,000 | 5 | 58.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 500,000 | 9 | 78.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 500,000 | 5 | 79.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 1,000,000 | 9 | 97.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 1,000,000 | 5 | 96.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 50,000 | 9 | 9.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 50,000 | 5 | 26.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 100,000 | 9 | 43.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 100,000 | 5 | 48.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 200,000 | 9 | 67.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 200,000 | 5 | 66.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 500,000 | 9 | 94.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 500,000 | 5 | 90.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 1,000,000 | 9 | 118.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 1,000,000 | 5 | 102.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 50,000 | 9 | 30.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 50,000 | 5 | 29.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 100,000 | 9 | 39.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 100,000 | 5 | 38.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 200,000 | 9 | 53.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 200,000 | 5 | 49.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 500,000 | 9 | 73.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 500,000 | 5 | 63.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k1-il | 1,000,000 | 9 | 80.7 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k1-il | 1,000,000 | 5 | 76.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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