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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(fx67k150-il) FX 67-K-150/17 AIRFOIL | Wortmann FX 67-K-150/17 airfoil Max thickness 15% at 40.2% chord Max camber 4.8% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(fx71l150-il) FX 71-L-150/30 AIRFOIL | Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx6617ai-il) WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) | Wortmann FX 66-17AII-182 airfoil (as tested at NASA) Max thickness 18.8% at 35.3% chord Max camber 3.7% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(fx74cl6140-il) FX 74-CL6-140 | Wortmann FX 74-CL6-140 airfoil Max thickness 14.1% at 30.9% chord Max camber 7.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(fx73cl1152-il) FX 73-CL1-152 | Wortmann FX 73-CL1-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.1% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(fx66h60-il) FX 66-H-60 | Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx67k150-il,fx71l150-il,fx6617ai-il,fx74cl6140-il,fx73cl1152-il,fx66h60-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx67k150-il | 50,000 | 9 | 5.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 50,000 | 5 | 14.3 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 100,000 | 9 | 25 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 100,000 | 5 | 27.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 200,000 | 9 | 61.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 200,000 | 5 | 68.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 500,000 | 9 | 126.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 500,000 | 5 | 118.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx67k150-il | 1,000,000 | 9 | 157.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx67k150-il | 1,000,000 | 5 | 147.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71l150-il | 50,000 | 9 | 27.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71l150-il | 50,000 | 5 | 26.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71l150-il | 100,000 | 9 | 39.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71l150-il | 100,000 | 5 | 35.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71l150-il | 200,000 | 9 | 47.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71l150-il | 200,000 | 5 | 40.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71l150-il | 500,000 | 9 | 51.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71l150-il | 500,000 | 5 | 49.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71l150-il | 1,000,000 | 9 | 59.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71l150-il | 1,000,000 | 5 | 58.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 50,000 | 9 | 4.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 50,000 | 5 | 8.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 100,000 | 9 | 6.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 100,000 | 5 | 29.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 200,000 | 9 | 62.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 200,000 | 5 | 68.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 500,000 | 9 | 109.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 500,000 | 5 | 105.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 1,000,000 | 9 | 137.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 1,000,000 | 5 | 130.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 50,000 | 9 | 5.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 50,000 | 5 | 18.9 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 9 | 19.9 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 100,000 | 5 | 40.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 9 | 48.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 200,000 | 5 | 72 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 9 | 114.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 500,000 | 5 | 120.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 9 | 157.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl6140-il | 1,000,000 | 5 | 158.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 50,000 | 9 | 4.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 50,000 | 5 | 20.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 9 | 24.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 100,000 | 5 | 42.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 9 | 53.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 200,000 | 5 | 68.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 9 | 100.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 500,000 | 5 | 106.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 9 | 137.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl1152-il | 1,000,000 | 5 | 136.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 50,000 | 9 | 28.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 50,000 | 5 | 29.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 100,000 | 9 | 37.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 100,000 | 5 | 40.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 200,000 | 9 | 51.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 200,000 | 5 | 51.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 500,000 | 9 | 69.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 500,000 | 5 | 67.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 1,000,000 | 9 | 84.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 1,000,000 | 5 | 76.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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