WORTMANN FX 74-080 (fx74080-il)
WORTMANN FX 74-080 - Wortmann FX 74-080 airfoil
| Details | Dat file | Parser | |
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(fx74080-il) WORTMANN FX 74-080 Wortmann FX 74-080 airfoil Max thickness 8.2% at 43.5% chord. Max camber 4.3% at 46.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
WORTMANN FX 74-080 1.00000 0.00000 0.99893 0.00127 0.99572 0.00237 0.99039 0.00383 0.98296 0.00557 0.97347 0.00767 0.96194 0.01014 0.94844 0.01297 0.93301 0.01622 0.91573 0.01989 0.89668 0.02391 0.87592 0.02826 0.85355 0.03296 0.82967 0.03805 0.80438 0.04354 0.77779 0.04936 0.75000 0.05535 0.72114 0.06119 0.69134 0.06647 0.66072 0.07098 0.62941 0.07470 0.59755 0.07778 0.56526 0.08027 0.53270 0.08217 0.50000 0.08339 0.46730 0.08386 0.43474 0.08357 0.40245 0.08258 0.37059 0.08097 0.33928 0.07883 0.30866 0.07617 0.27886 0.07306 0.25000 0.06953 0.22221 0.06562 0.19562 0.06138 0.17033 0.05686 0.14645 0.05209 0.12408 0.04713 0.10332 0.04205 0.08427 0.03691 0.06699 0.03176 0.05156 0.02667 0.03806 0.02173 0.02653 0.01702 0.01704 0.01266 0.00961 0.00881 0.00428 0.00543 0.00107 0.00248 0.00000 0.00000 0.00107 -0.00204 0.00428 -0.00359 0.00961 -0.00472 0.01704 -0.00551 0.02653 -0.00593 0.03806 -0.00609 0.05156 -0.00605 0.06699 -0.00584 0.08427 -0.00549 0.10332 -0.00505 0.12408 -0.00452 0.14645 -0.00393 0.17033 -0.00329 0.19562 -0.00263 0.22221 -0.00196 0.25000 -0.00129 0.27886 -0.00064 0.30866 -0.00001 0.33928 0.00058 0.37059 0.00113 0.40245 0.00162 0.43474 0.00206 0.46730 0.00243 0.50000 0.00275 0.53270 0.00305 0.56526 0.00335 0.59755 0.00364 0.62941 0.00388 0.66072 0.00403 0.69134 0.00407 0.72114 0.00412 0.75000 0.00436 0.77779 0.00489 0.80438 0.00560 0.82967 0.00625 0.85355 0.00662 0.87592 0.00667 0.89668 0.00644 0.91573 0.00600 0.93301 0.00539 0.94844 0.00460 0.96194 0.00368 0.97347 0.00270 0.98296 0.00174 0.99039 0.00080 0.99572 0.00009 0.99893 0.00002 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 WORTMANN FX 74-080 (fx74080-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74080-il | 50,000 | 9 | 24.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 50,000 | 5 | 27.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 9 | 39.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 5 | 58 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 9 | 80.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 5 | 87 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 9 | 134.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 5 | 131.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 9 | 173.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 5 | 164.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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