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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(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 |
(be50sm-il) BE50 (smoothed) | Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 23.8% chord Max camber 4% at 45.4% chord | Remove Airfoil details Airfoil plotter |
(ames03-il) NASA/AMES A-03 AIRFOIL | NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord | Remove Airfoil details Airfoil plotter |
(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (c5a-il,be50sm-il,ames03-il,c141f-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| be50sm-il | 50,000 | 9 | 38.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 50,000 | 5 | 43 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 100,000 | 9 | 60.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 100,000 | 5 | 59.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 200,000 | 9 | 81.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 200,000 | 5 | 74.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 500,000 | 9 | 104.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 500,000 | 5 | 97.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 1,000,000 | 9 | 121.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 1,000,000 | 5 | 115.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 50,000 | 9 | 27.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 50,000 | 5 | 27.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 100,000 | 9 | 34.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 100,000 | 5 | 39.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 200,000 | 9 | 50.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 200,000 | 5 | 53.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 500,000 | 9 | 72.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 500,000 | 5 | 70.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 1,000,000 | 9 | 87.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 1,000,000 | 5 | 83.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 50,000 | 9 | 34.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 50,000 | 5 | 32.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 9 | 50.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 5 | 46.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 9 | 69.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 5 | 59.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 9 | 89 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 5 | 70 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 9 | 89.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 5 | 86.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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