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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(naca661212-il) NACA 66(1)-212 | NACA 66(1)-212 airfoil Max thickness 12% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(ah83150q-il) AH 83-150 Q | Althaus AH 83-150 Q airfoil Max thickness 15% at 40.2% chord Max camber 4.1% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(naca747a415-il) NACA 747A415 | NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord | Remove Airfoil details Airfoil plotter |
(fx78pk188-il) FX 78-PK-188/20 | Wortmann FX 78-PK-188/20 variable geometry airfoil Max thickness 18.8% at 43.5% chord Max camber 2.4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca661212-il,ah83150q-il,naca747a415-il,fx78pk188-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca661212-il | 50,000 | 9 | 22 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 50,000 | 5 | 22.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 100,000 | 9 | 37.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 100,000 | 5 | 32.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 200,000 | 9 | 47.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 200,000 | 5 | 46.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 500,000 | 9 | 71.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 500,000 | 5 | 62.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca661212-il | 1,000,000 | 9 | 86 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca661212-il | 1,000,000 | 5 | 70.5 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 50,000 | 9 | 6.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 50,000 | 5 | 15.9 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 100,000 | 9 | 39.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 100,000 | 5 | 35.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 200,000 | 9 | 73.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 200,000 | 5 | 71.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 500,000 | 9 | 109.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 500,000 | 5 | 102.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 1,000,000 | 9 | 134.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 1,000,000 | 5 | 122.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 9 | 19 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 5 | 17 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 9 | 37.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 5 | 44.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 5 | 66.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 9 | 97.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 5 | 92.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 9 | 120.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 5 | 110.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 50,000 | 9 | 18.6 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 50,000 | 5 | 14.9 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 100,000 | 9 | 24.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 100,000 | 5 | 22.9 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 200,000 | 9 | 38.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 200,000 | 5 | 37.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 500,000 | 9 | 92.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 500,000 | 5 | 91 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 1,000,000 | 9 | 129.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 1,000,000 | 5 | 118.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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