FX 66-H-80 (fx66h80-il)
FX 66-H-80 - Wortmann FX 66-H-80 airfoil
| Details | Dat file | Parser | |
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(fx66h80-il) FX 66-H-80 Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord. Max camber 2.5% at 25% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 66-H-80 1.00000 0.00000 0.99893 0.00001 0.99572 0.00002 0.99039 0.00020 0.98296 0.00048 0.97347 0.00082 0.96194 0.00121 0.94844 0.00167 0.93301 0.00226 0.91573 0.00300 0.89668 0.00395 0.87592 0.00510 0.85355 0.00651 0.82967 0.00821 0.80438 0.01023 0.77779 0.01258 0.75000 0.01526 0.72114 0.01823 0.69134 0.02147 0.66072 0.02491 0.62941 0.02854 0.59755 0.03235 0.56526 0.03630 0.53270 0.04033 0.50000 0.04435 0.46730 0.04830 0.43474 0.05215 0.40245 0.05581 0.37059 0.05910 0.33928 0.06177 0.30866 0.06362 0.27886 0.06454 0.25000 0.06455 0.22221 0.06365 0.19562 0.06179 0.17033 0.05902 0.14645 0.05546 0.12408 0.05130 0.10332 0.04669 0.08427 0.04174 0.06699 0.03658 0.05156 0.03130 0.03806 0.02600 0.02653 0.02080 0.01704 0.01581 0.00961 0.01122 0.00428 0.00705 0.00107 0.00326 0.00000 0.00000 0.00107 -0.00271 0.00428 -0.00484 0.00961 -0.00659 0.01704 -0.00811 0.02653 -0.00936 0.03806 -0.01042 0.05156 -0.01130 0.06699 -0.01205 0.08427 -0.01266 0.10332 -0.01318 0.12408 -0.01360 0.14645 -0.01397 0.17033 -0.01431 0.19562 -0.01459 0.22221 -0.01486 0.25000 -0.01515 0.27886 -0.01548 0.30866 -0.01583 0.33928 -0.01619 0.37059 -0.01655 0.40245 -0.01688 0.43474 -0.01718 0.46730 -0.01742 0.50000 -0.01758 0.53270 -0.01765 0.56526 -0.01762 0.59755 -0.01748 0.62941 -0.01724 0.66072 -0.01690 0.69134 -0.01646 0.72114 -0.01592 0.75000 -0.01527 0.77779 -0.01451 0.80438 -0.01362 0.82967 -0.01258 0.85355 -0.01139 0.87592 -0.01010 0.89668 -0.00877 0.91573 -0.00747 0.93301 -0.00621 0.94844 -0.00501 0.96194 -0.00390 0.97347 -0.00287 0.98296 -0.00194 0.99039 -0.00115 0.99572 -0.00054 0.99893 -0.00008 1.00000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for FX 66-H-80 (fx66h80-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66h80-il | 50,000 | 9 | 32.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 50,000 | 5 | 31.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 9 | 47.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 5 | 47.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 9 | 63 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 5 | 62.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 9 | 87.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 5 | 83.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 9 | 105.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 5 | 98.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||