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 |
(dga1138-il) D.G.A. 1138 | D.G.A. 1138 airfoil Max thickness 6.9% at 30% chord Max camber 2.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(hq2590sm-il) HQ 2.5/9.0 smoothed by Eppler | Quabeck HQ 2.5/9 R/C sailplane airfoil (smoothed) Max thickness 9% at 35% chord Max camber 2.5% at 55% chord | Remove Airfoil details Airfoil plotter |
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Polars for (c5a-il,dga1138-il,hq2590sm-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 | |
| dga1138-il | 50,000 | 9 | 38.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 50,000 | 5 | 37.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 100,000 | 9 | 54.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 100,000 | 5 | 49.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 200,000 | 9 | 69.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 200,000 | 5 | 57.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 500,000 | 9 | 79.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 500,000 | 5 | 67.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 1,000,000 | 9 | 86.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 1,000,000 | 5 | 77 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2590sm-il | 50,000 | 9 | 39 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2590sm-il | 50,000 | 5 | 39.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2590sm-il | 100,000 | 9 | 58.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2590sm-il | 100,000 | 5 | 56.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2590sm-il | 200,000 | 9 | 79.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2590sm-il | 200,000 | 5 | 73.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2590sm-il | 500,000 | 9 | 105.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2590sm-il | 500,000 | 5 | 84.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2590sm-il | 1,000,000 | 9 | 112.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2590sm-il | 1,000,000 | 5 | 91.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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