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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(hq3015-il) HQ 3.0/15 AIRFOIL | Quabeck HQ 3.0/15 R/C sailplane airfoil Max thickness 15% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca16009-il) NACA 16009 | NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca0021-il) NACA 0021 | NACA 0021 airfoil Max thickness 21% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ah93w480b-il) AH 93-W-480B | Althaus AH 93-W-480B airfoil for use on wind turbines (W) Max thickness 47.8% at 44.1% chord Max camber 3.6% at 44.1% chord | Remove Airfoil details Airfoil plotter |
(hq259-il) HQ 2.5/9 AIRFOIL | Quabeck HQ 2.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq3015-il,naca16009-il,naca0021-il,ah93w480b-il,hq259-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq3015-il | 50,000 | 9 | 25.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 50,000 | 5 | 30.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 100,000 | 9 | 52.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 100,000 | 5 | 51.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 200,000 | 9 | 75.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 200,000 | 5 | 67.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 500,000 | 9 | 97.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 500,000 | 5 | 84 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 1,000,000 | 9 | 111.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 1,000,000 | 5 | 95.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 50,000 | 9 | 18 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 50,000 | 5 | 19.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 100,000 | 9 | 25.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 100,000 | 5 | 28.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 200,000 | 9 | 39.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 200,000 | 5 | 34.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 500,000 | 9 | 44.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 500,000 | 5 | 38 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16009-il | 1,000,000 | 9 | 47 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16009-il | 1,000,000 | 5 | 47.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 50,000 | 9 | 19.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 50,000 | 5 | 25.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 100,000 | 9 | 36.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 100,000 | 5 | 35.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 200,000 | 9 | 48 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 200,000 | 5 | 43.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 500,000 | 9 | 60.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 500,000 | 5 | 56.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 1,000,000 | 9 | 74.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 1,000,000 | 5 | 71 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w480b-il | 50,000 | 9 | 7.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w480b-il | 50,000 | 5 | 11.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w480b-il | 100,000 | 9 | 18.3 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w480b-il | 100,000 | 5 | 20.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w480b-il | 200,000 | 9 | 21.4 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w480b-il | 200,000 | 5 | 22.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w480b-il | 500,000 | 9 | 24.9 at α=14.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w480b-il | 500,000 | 5 | 23.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w480b-il | 1,000,000 | 9 | 28 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w480b-il | 1,000,000 | 5 | 26.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259-il | 50,000 | 9 | 38.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259-il | 50,000 | 5 | 39.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259-il | 100,000 | 9 | 58.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259-il | 100,000 | 5 | 56.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259-il | 200,000 | 9 | 80 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259-il | 200,000 | 5 | 73 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259-il | 500,000 | 9 | 106.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259-il | 500,000 | 5 | 88.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259-il | 1,000,000 | 9 | 122 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259-il | 1,000,000 | 5 | 92.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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