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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(e64-il) E64 (8.45%) | Eppler E64 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.9% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(pw51-pw) PW51 | Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord Max camber 1.4% at 27.5% chord | Remove Airfoil details Airfoil plotter |
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(hq3012-il) HQ 3.0/12 AIRFOIL | Quabeck HQ 3.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(e521-il) EPPLER 521 AIRFOIL | Eppler E521 tailplane airfoil Max thickness 13.8% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e67-il) EPPLER 67 AIRFOIL | Eppler E67 low Reynolds number airfoil Max thickness 11.6% at 32.6% chord Max camber 3.7% at 51.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e64-il,pw51-pw,c5e-il,hq3012-il,e521-il,e67-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e64-il | 50,000 | 9 | 41.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 100,000 | 9 | 64 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 100,000 | 5 | 62.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 200,000 | 9 | 88.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 200,000 | 5 | 81.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 500,000 | 9 | 120.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 500,000 | 5 | 103.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 1,000,000 | 9 | 140.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 1,000,000 | 5 | 113.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pw51-pw | 50,000 | 9 | 26.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 100,000 | 9 | 41.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 200,000 | 9 | 56.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 500,000 | 9 | 76.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 1,000,000 | 9 | 90.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 2,000,000 | 9 | 104.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw51-pw | 5,000,000 | 9 | 119.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 50,000 | 9 | 31.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 50,000 | 5 | 31.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 5 | 42.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 9 | 59.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 5 | 47.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 9 | 67.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 9 | 77.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 5 | 81 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3012-il | 50,000 | 9 | 34.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3012-il | 50,000 | 5 | 36.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3012-il | 100,000 | 9 | 57.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3012-il | 100,000 | 5 | 56.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3012-il | 200,000 | 9 | 80.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3012-il | 200,000 | 5 | 75.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3012-il | 500,000 | 9 | 109.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3012-il | 500,000 | 5 | 88.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3012-il | 1,000,000 | 9 | 117.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3012-il | 1,000,000 | 5 | 98.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 50,000 | 9 | 29.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 50,000 | 5 | 29.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 100,000 | 9 | 43.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 100,000 | 5 | 34.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 200,000 | 9 | 44.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 200,000 | 5 | 43.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 500,000 | 9 | 58.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 500,000 | 5 | 56.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 9 | 70 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 5 | 66.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 50,000 | 5 | 36.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 100,000 | 9 | 60.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 100,000 | 5 | 60.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 200,000 | 9 | 86.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 200,000 | 5 | 82.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 500,000 | 9 | 121.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 500,000 | 5 | 107.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 9 | 144.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 5 | 117.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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