FX 74-CL6-140 (fx74cl6140-il)
FX 74-CL6-140 - Wortmann FX 74-CL6-140 airfoil
| Details | Dat file | Parser | |
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(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 Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 74-CL6-140 1.00000 0.00000 0.99893 0.00037 0.99572 0.00164 0.99039 0.00342 0.98296 0.00574 0.97347 0.00846 0.96194 0.01154 0.94844 0.01496 0.93301 0.01869 0.91573 0.02277 0.89668 0.02724 0.87592 0.03213 0.85355 0.03742 0.82967 0.04303 0.80438 0.04892 0.77779 0.05513 0.75000 0.06159 0.72114 0.06828 0.69134 0.07517 0.66072 0.08219 0.62941 0.08933 0.59755 0.09654 0.56526 0.10379 0.53270 0.11100 0.50000 0.11809 0.46730 0.12491 0.43474 0.13110 0.40245 0.13615 0.37059 0.13958 0.33928 0.14115 0.30866 0.14093 0.27886 0.13910 0.25000 0.13580 0.22221 0.13115 0.19562 0.12525 0.17033 0.11826 0.14645 0.11037 0.12408 0.10174 0.10332 0.09250 0.08427 0.08281 0.06699 0.07280 0.05156 0.06262 0.03806 0.05247 0.02653 0.04259 0.01704 0.03304 0.00961 0.02402 0.00428 0.01533 0.00107 0.00701 0.00000 0.00000 0.00107 -0.00514 0.00428 -0.00819 0.00961 -0.00993 0.01704 -0.01115 0.02653 -0.01188 0.03806 -0.01223 0.05156 -0.01220 0.06699 -0.01181 0.08427 -0.01106 0.10332 -0.01003 0.12408 -0.00886 0.14645 -0.00759 0.17033 -0.00627 0.19562 -0.00491 0.22221 -0.00353 0.25000 -0.00217 0.27886 -0.00086 0.30866 0.00039 0.33928 0.00157 0.37059 0.00267 0.40245 0.00371 0.43474 0.00471 0.46730 0.00571 0.50000 0.00679 0.53270 0.00795 0.56526 0.00927 0.59755 0.01088 0.62941 0.01285 0.66072 0.01507 0.69134 0.01722 0.72114 0.01899 0.75000 0.02016 0.77779 0.02069 0.80438 0.02062 0.82967 0.02001 0.85355 0.01890 0.87592 0.01736 0.89668 0.01553 0.91573 0.01349 0.93301 0.01135 0.94844 0.00913 0.96194 0.00696 0.97347 0.00497 0.98296 0.00326 0.99039 0.00188 0.99572 0.00087 0.99893 0.00020 1.00000 0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for FX 74-CL6-140 (fx74cl6140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
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