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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(k2-il) GRUMMAN K-2 AIRFOIL | Grumman K-2 transonic airfoil (GAC .80-.53-10.3) Max thickness 10.3% at 38.9% chord Max camber 1.3% at 88.3% chord | Remove Airfoil details Airfoil plotter |
(usa40b-il) USA 40 B AIRFOIL | USA-40B airfoil Max thickness 13.6% at 20% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% chord | Remove Airfoil details Airfoil plotter |
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL | NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
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Polars for (k2-il,usa40b-il,c5a-il,ls417-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| k2-il | 50,000 | 9 | 21.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 50,000 | 5 | 21.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 100,000 | 9 | 28.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 100,000 | 5 | 25.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 200,000 | 9 | 29 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 200,000 | 5 | 35.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 500,000 | 9 | 44 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 500,000 | 5 | 52.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 1,000,000 | 9 | 60.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 1,000,000 | 5 | 66.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 50,000 | 9 | 25.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 50,000 | 5 | 31.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 100,000 | 9 | 39.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 100,000 | 5 | 45.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 200,000 | 9 | 56.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 200,000 | 5 | 62 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 500,000 | 9 | 85.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 500,000 | 5 | 88.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 1,000,000 | 9 | 111.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 1,000,000 | 5 | 112 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 9 | 27.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 5 | 32.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 9 | 44.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 5 | 40.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 9 | 56.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 5 | 55.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 9 | 68.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 5 | 72.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 50,000 | 9 | 29.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 50,000 | 5 | 25 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 100,000 | 9 | 42.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 100,000 | 5 | 41 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 200,000 | 9 | 61 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 200,000 | 5 | 61.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 500,000 | 9 | 92.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 500,000 | 5 | 82.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 1,000,000 | 9 | 112.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 1,000,000 | 5 | 91.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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