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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(ah93w174-il) AH 93-W-174 | Althaus AH 93-W-174 airfoil for use on wind turbines (W) Max thickness 17.4% at 33.9% chord Max camber 3.9% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx66s161-il) FX 66-S-161 AIRFOIL | Wortmann FX 66-S-161 airfoil Max thickness 16.1% at 33.9% chord Max camber 3.9% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(fx69h083-il) BELL/WORTMANN FX 69-H-083 AIRFOIL | Bell/Wortmann FX 69-H-083 rotorcraft airfoil Max thickness 8.4% at 33.3% chord Max camber 2.5% at 33.3% chord | Remove Airfoil details Airfoil plotter |
(ah79100c-il) AH 79-100 C AIRFOIL | Althaus AH 79-100C airfoil Max thickness 9.9% at 30.9% chord Max camber 6.7% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx77w258-il) WORTMANN FX 77-W-258 AIRFOIL | Wortmann FX 77-W-258 wind turbine airfoil Max thickness 26.1% at 30.9% chord Max camber 4.3% at 27.9% chord | Remove Airfoil details Airfoil plotter |
(naca0018-il) NACA 0018 | NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ah79100b-il) AH 79-100 B AIRFOIL | Althaus AH 79-100B airfoil Max thickness 10% at 30.9% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ah93w174-il,fx66s161-il,fx69h083-il,ah79100c-il,fx77w258-il,naca0018-il,ah79100b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah93w174-il | 50,000 | 9 | 4.7 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w174-il | 50,000 | 5 | 11.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w174-il | 100,000 | 9 | 8.5 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w174-il | 100,000 | 5 | 33 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w174-il | 200,000 | 9 | 65.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w174-il | 200,000 | 5 | 71.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w174-il | 500,000 | 9 | 113.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w174-il | 500,000 | 5 | 112.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w174-il | 1,000,000 | 9 | 148.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w174-il | 1,000,000 | 5 | 138.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 50,000 | 9 | 5.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 50,000 | 5 | 16.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 9 | 16.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 5 | 42.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 9 | 73.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 5 | 75.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 9 | 116 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 5 | 114.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 9 | 148.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 5 | 134.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 50,000 | 9 | 36.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 50,000 | 5 | 37 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 100,000 | 9 | 53 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 100,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 200,000 | 9 | 69.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 200,000 | 5 | 66.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 500,000 | 9 | 90.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 500,000 | 5 | 78.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 1,000,000 | 9 | 101 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 1,000,000 | 5 | 81.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 50,000 | 9 | 32.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 50,000 | 5 | 31.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 100,000 | 9 | 61.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 100,000 | 5 | 61.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 200,000 | 9 | 97.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 200,000 | 5 | 97 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 500,000 | 9 | 147.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 500,000 | 5 | 137.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100c-il | 1,000,000 | 9 | 183 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100c-il | 1,000,000 | 5 | 161.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 50,000 | 9 | 1.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 50,000 | 5 | 2.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 100,000 | 9 | 1.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 100,000 | 5 | 10.5 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 200,000 | 9 | 9.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 200,000 | 5 | 36.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 500,000 | 9 | 76 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 500,000 | 5 | 83.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 1,000,000 | 9 | 112.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 1,000,000 | 5 | 103.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 5 | 26.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 9 | 37.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 5 | 38.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 9 | 50.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 5 | 48 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 9 | 65.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 5 | 61.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 9 | 77.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 5 | 73.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 50,000 | 9 | 32.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 50,000 | 5 | 32.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 9 | 65.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 5 | 68.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 9 | 100 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 5 | 101 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 9 | 148.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 5 | 139.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 9 | 183.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 5 | 153.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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