WORTMANN FX 80-080 (fx80080-il)
WORTMANN FX 80-080 - Wortmann FX 80-080 airfoil
| Details | Dat file | Parser | |
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(fx80080-il) WORTMANN FX 80-080 Wortmann FX 80-080 airfoil Max thickness 8.1% at 40.2% chord. Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
WORTMANN FX 80-080 1.00000 0.00000 0.99893 0.00111 0.99572 0.00200 0.99039 0.00326 0.98296 0.00483 0.97347 0.00664 0.96194 0.00867 0.94844 0.01089 0.93301 0.01336 0.91573 0.01606 0.89668 0.01901 0.87592 0.02218 0.85355 0.02561 0.82967 0.02927 0.80438 0.03316 0.77779 0.03716 0.75000 0.04122 0.72114 0.04505 0.69134 0.04876 0.66072 0.05207 0.62941 0.05503 0.59755 0.05738 0.56526 0.05926 0.53270 0.06062 0.50000 0.06153 0.46730 0.06199 0.43474 0.06207 0.40245 0.06175 0.37059 0.06110 0.33928 0.06007 0.30866 0.05872 0.27886 0.05704 0.25000 0.05507 0.22221 0.05279 0.19562 0.05027 0.17033 0.04748 0.14645 0.04449 0.12408 0.04127 0.10332 0.03789 0.08427 0.03433 0.06699 0.03066 0.05156 0.02686 0.03806 0.02297 0.02653 0.01897 0.01704 0.01492 0.00961 0.01082 0.00428 0.00692 0.00107 0.00313 0.00000 0.00000 0.00107 -0.00259 0.00428 -0.00516 0.00961 -0.00738 0.01704 -0.00942 0.02653 -0.01117 0.03806 -0.01267 0.05156 -0.01394 0.06699 -0.01502 0.08427 -0.01593 0.10332 -0.01673 0.12408 -0.01739 0.14645 -0.01797 0.17033 -0.01842 0.19562 -0.01881 0.22221 -0.01907 0.25000 -0.01927 0.27886 -0.01936 0.30866 -0.01938 0.33928 -0.01929 0.37059 -0.01912 0.40245 -0.01885 0.43474 -0.01849 0.46730 -0.01799 0.50000 -0.01741 0.53270 -0.01662 0.56526 -0.01568 0.59755 -0.01448 0.62941 -0.01305 0.66072 -0.01129 0.69134 -0.00942 0.72114 -0.00737 0.75000 -0.00542 0.77779 -0.00344 0.80438 -0.00170 0.82967 -0.00021 0.85355 0.00091 0.87592 0.00170 0.89668 0.00215 0.91573 0.00234 0.93301 0.00228 0.94844 0.00203 0.96194 0.00163 0.97347 0.00116 0.98296 0.00067 0.99039 0.00018 0.99572 0.00024 0.99893 0.00057 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 80-080 (fx80080-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx80080-il | 50,000 | 9 | 33.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 50,000 | 5 | 36.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 100,000 | 9 | 57.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 100,000 | 5 | 55.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 200,000 | 9 | 80.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 200,000 | 5 | 74.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 500,000 | 9 | 113.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 500,000 | 5 | 90.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 1,000,000 | 9 | 123.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 1,000,000 | 5 | 98 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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