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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(naca66-018-il) NACA 66-018 | NACA 66-018 airfoil Max thickness 18% at 45% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(hq2195-il) HQ 2.1/9.5 AIRFOIL | Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord Max camber 2.1% at 55% chord | Remove Airfoil details Airfoil plotter |
(e473-il) EPPLER 473 AIRFOIL | Eppler E473 aerobatic aircraft airfoil Max thickness 16.2% at 21.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca66-018-il,hq2195-il,e473-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca66-018-il | 50,000 | 9 | 20.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 50,000 | 5 | 15.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 9 | 31.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 5 | 18.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 9 | 31 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 5 | 34.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 9 | 57.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 5 | 50.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 9 | 72 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 5 | 57.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 50,000 | 9 | 37.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 50,000 | 5 | 37.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 5 | 52.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 9 | 74.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 5 | 67.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 9 | 96.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 5 | 79 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 9 | 101 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 50,000 | 9 | 15.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 50,000 | 5 | 21.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 100,000 | 9 | 26.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 100,000 | 5 | 35.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 200,000 | 9 | 47.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 200,000 | 5 | 53.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 500,000 | 9 | 78.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 500,000 | 5 | 78.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 1,000,000 | 9 | 101.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 1,000,000 | 5 | 95.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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