FX 72-LS-160 (fx72ls160-il)
FX 72-LS-160 - Wortmann FX 72-LS-160 airfoil
| Details | Dat file | Parser | |
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(fx72ls160-il) FX 72-LS-160 Wortmann FX 72-LS-160 airfoil Max thickness 16% at 37.1% chord. Max camber 8.2% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 72-LS-160 1.00000 0.00000 0.99893 0.00037 0.99572 0.00147 0.99039 0.00330 0.98296 0.00584 0.97347 0.00910 0.96194 0.01305 0.94844 0.01769 0.93301 0.02297 0.91573 0.02887 0.89668 0.03540 0.87592 0.04252 0.85355 0.05022 0.82967 0.05841 0.80438 0.06707 0.77779 0.07620 0.75000 0.08579 0.72114 0.09579 0.69134 0.10605 0.66072 0.11639 0.62941 0.12656 0.59755 0.13615 0.56526 0.14458 0.53270 0.15139 0.50000 0.15643 0.46730 0.15982 0.43474 0.16164 0.40245 0.16188 0.37059 0.16058 0.33928 0.15792 0.30866 0.15415 0.27886 0.14937 0.25000 0.14365 0.22221 0.13710 0.19562 0.12980 0.17033 0.12184 0.14645 0.11333 0.12408 0.10432 0.10332 0.09493 0.08427 0.08525 0.06699 0.07544 0.05156 0.06553 0.03806 0.05557 0.02653 0.04580 0.01704 0.03634 0.00961 0.02746 0.00428 0.01815 0.00107 0.00834 0.00000 0.00000 0.00107 -0.00583 0.00428 -0.00890 0.00961 -0.01096 0.01704 -0.01313 0.02653 -0.01470 0.03806 -0.01563 0.05156 -0.01591 0.06699 -0.01568 0.08427 -0.01512 0.10332 -0.01424 0.12408 -0.01318 0.14645 -0.01196 0.17033 -0.01054 0.19562 -0.00904 0.22221 -0.00746 0.25000 -0.00582 0.27886 -0.00420 0.30866 -0.00259 0.33928 -0.00103 0.37059 0.00046 0.40245 0.00188 0.43474 0.00321 0.46730 0.00443 0.50000 0.00553 0.53270 0.00649 0.56526 0.00731 0.59755 0.00799 0.62941 0.00856 0.66072 0.00898 0.69134 0.00929 0.72114 0.00948 0.75000 0.00959 0.77779 0.00970 0.80438 0.00987 0.82967 0.01007 0.85355 0.01023 0.87592 0.01029 0.89668 0.01017 0.91573 0.00982 0.93301 0.00916 0.94844 0.00817 0.96194 0.00690 0.97347 0.00542 0.98296 0.00390 0.99039 0.00250 0.99572 0.00135 0.99893 0.00044 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 72-LS-160 (fx72ls160-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx72ls160-il | 50,000 | 9 | 5.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72ls160-il | 50,000 | 5 | 8.4 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72ls160-il | 100,000 | 9 | 14.5 at α=17.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72ls160-il | 100,000 | 5 | 13.3 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72ls160-il | 200,000 | 9 | 22.3 at α=15° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72ls160-il | 200,000 | 5 | 58.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72ls160-il | 500,000 | 9 | 121.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72ls160-il | 500,000 | 5 | 125.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72ls160-il | 1,000,000 | 9 | 175.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72ls160-il | 1,000,000 | 5 | 174.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||