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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(e543-il) EPPLER 543 AIRFOIL | Eppler E543 general aviation airfoil Max thickness 17.2% at 40.7% chord Max camber 1.9% at 31% chord | Remove Airfoil details Airfoil plotter |
(m5-il) NACA M5 AIRFOIL | NACA/Munk M-5 airfoil Max thickness 8.2% at 30.1% chord Max camber 2.1% at 30.1% chord | Remove Airfoil details Airfoil plotter |
(e858-il) EPPLER 858 AIRFOIL | Eppler E858 propeller airfoil Max thickness 22.7% at 26.6% chord Max camber 4.7% at 44.3% chord | Remove Airfoil details Airfoil plotter |
(goe566-il) GOE 566 AIRFOIL | Gottingen 566 airfoil Max thickness 8.7% at 30% chord Max camber 2.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(hq09-il) HQ 0/9 AIRFOIL | Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e543-il,m5-il,e858-il,goe566-il,hq09-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e543-il | 50,000 | 9 | 21.3 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 50,000 | 5 | 17.9 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 100,000 | 9 | 42.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 100,000 | 5 | 35.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 200,000 | 9 | 56.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 200,000 | 5 | 58.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 500,000 | 9 | 86.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 500,000 | 5 | 82.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 1,000,000 | 9 | 108.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 1,000,000 | 5 | 98.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 50,000 | 9 | 32.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 50,000 | 5 | 34 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 100,000 | 9 | 47.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 100,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 200,000 | 9 | 60.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 200,000 | 5 | 57.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 500,000 | 9 | 76.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 500,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 9 | 86.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 5 | 76.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 50,000 | 9 | 3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 50,000 | 5 | 13 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 100,000 | 9 | 21.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 100,000 | 5 | 34.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 200,000 | 9 | 48.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 200,000 | 5 | 51.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 500,000 | 9 | 73.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 500,000 | 5 | 67.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 1,000,000 | 9 | 88.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 1,000,000 | 5 | 87.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 50,000 | 9 | 34.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 50,000 | 5 | 36.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 100,000 | 9 | 52.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 100,000 | 5 | 50.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 200,000 | 9 | 70 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 200,000 | 5 | 61.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 500,000 | 9 | 88.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 500,000 | 5 | 79.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe566-il | 1,000,000 | 9 | 97.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe566-il | 1,000,000 | 5 | 90 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 50,000 | 9 | 27.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 50,000 | 5 | 26 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 9 | 36.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 5 | 33.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 9 | 46.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 5 | 38.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 9 | 51.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 5 | 53.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 9 | 64.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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