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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(n0011sc-il) NACA/LANGLEY SYMMETRICAL | NASA/Langley 11% symmetrical supercritical airfoil Max thickness 11% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(dae51-il) DAE-51 AIRFOIL | Drela DAE51 low Reynolds number airfoil Max thickness 9.4% at 30.7% chord Max camber 4% at 46.4% chord | Remove Airfoil details Airfoil plotter |
(e1213-il) EPPLER 1213 AIRFOIL | Eppler E1213 general aviation airfoil Max thickness 17.4% at 22.1% chord Max camber 2.1% at 35.1% chord | Remove Airfoil details Airfoil plotter |
(hq158-il) HQ 1.5/8 AIRFOIL | Quabeck HQ 1.5/8 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n0011sc-il,dae51-il,e1213-il,hq158-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n0011sc-il | 50,000 | 9 | 22.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 50,000 | 5 | 22.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 100,000 | 9 | 30.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 100,000 | 5 | 30.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 200,000 | 9 | 41.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 200,000 | 5 | 39.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 500,000 | 9 | 49.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 500,000 | 5 | 50.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 1,000,000 | 9 | 59 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 1,000,000 | 5 | 62.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 50,000 | 9 | 39.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 50,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 9 | 62.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 5 | 63.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 5 | 84.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 9 | 121.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 5 | 110.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 5 | 127.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 50,000 | 9 | 11.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 50,000 | 5 | 22.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 5 | 39.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 9 | 51.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 5 | 55.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 9 | 79.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 5 | 80.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 9 | 102.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 5 | 101.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 50,000 | 9 | 35.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 50,000 | 5 | 35.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 100,000 | 9 | 51.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 100,000 | 5 | 49 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 200,000 | 9 | 68.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 200,000 | 5 | 60.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 500,000 | 9 | 86.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 500,000 | 5 | 70 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 1,000,000 | 9 | 92 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 1,000,000 | 5 | 77.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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