Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Reynolds number: 500,000 Max Cl/Cd: 32.43 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel10-il-500000.txt Download as CSV file: xf-eiffel10-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5835 0.16989 0.16726 0.0292 1.0000 0.0108
-13.500 -0.5758 0.16677 0.16414 0.0278 1.0000 0.0109
-13.250 -0.5681 0.16367 0.16104 0.0264 1.0000 0.0110
-13.000 -0.5603 0.16054 0.15792 0.0250 1.0000 0.0111
-12.750 -0.5526 0.15743 0.15481 0.0237 1.0000 0.0111
-12.500 -0.5449 0.15434 0.15172 0.0223 1.0000 0.0112
-12.250 -0.5372 0.15126 0.14865 0.0210 1.0000 0.0112
-12.000 -0.5294 0.14818 0.14557 0.0196 1.0000 0.0112
-11.750 -0.5216 0.14513 0.14252 0.0182 1.0000 0.0112
-11.500 -0.5139 0.14211 0.13951 0.0167 1.0000 0.0113
-11.250 -0.5061 0.13913 0.13653 0.0152 1.0000 0.0113
-9.000 -0.4353 0.11374 0.11124 0.0007 1.0000 0.0114
-8.750 -0.4258 0.10998 0.10749 0.0005 1.0000 0.0114
-8.500 -0.4169 0.10676 0.10429 -0.0002 1.0000 0.0114
-8.250 -0.4083 0.10379 0.10134 -0.0012 1.0000 0.0114
-8.000 -0.3997 0.10095 0.09853 -0.0023 1.0000 0.0115
-7.750 -0.3908 0.09822 0.09582 -0.0036 1.0000 0.0115
-7.500 -0.3797 0.09537 0.09299 -0.0056 1.0000 0.0116
-7.250 -0.3666 0.09245 0.09009 -0.0080 1.0000 0.0116
-7.000 -0.3523 0.08951 0.08718 -0.0107 1.0000 0.0117
-6.750 -0.3368 0.08656 0.08426 -0.0136 1.0000 0.0117
-6.500 -0.3202 0.08361 0.08133 -0.0166 1.0000 0.0118
-6.250 -0.3026 0.08066 0.07841 -0.0198 1.0000 0.0119
-6.000 -0.2843 0.07775 0.07552 -0.0230 1.0000 0.0120
-5.750 -0.2449 0.07352 0.07126 -0.0314 0.9650 0.0121
-5.500 -0.2190 0.07035 0.06796 -0.0356 0.9100 0.0123
-5.250 -0.1979 0.06761 0.06507 -0.0384 0.8705 0.0125
-5.000 -0.1744 0.06483 0.06210 -0.0416 0.8268 0.0127
-4.750 -0.1474 0.06193 0.05901 -0.0455 0.7899 0.0130
-4.500 -0.1135 0.05901 0.05583 -0.0508 0.7406 0.0134
-4.250 -0.0521 0.04009 0.03495 -0.0557 0.0370 0.0135
-4.000 -0.0382 0.03697 0.03183 -0.0554 0.0320 0.0136
-3.750 -0.0195 0.05257 0.04699 -0.0644 0.0304 0.0136
-3.500 0.0074 0.04999 0.04440 -0.0669 0.0293 0.0138
-3.250 0.0399 0.04751 0.04188 -0.0704 0.0288 0.0141
-3.000 0.0749 0.04503 0.03936 -0.0741 0.0287 0.0144
-2.750 0.1108 0.04261 0.03688 -0.0777 0.0289 0.0146
-2.500 0.1472 0.04030 0.03450 -0.0812 0.0294 0.0148
-2.250 0.1840 0.03811 0.03223 -0.0843 0.0301 0.0150
-2.000 0.2214 0.03604 0.03007 -0.0873 0.0312 0.0153
-1.750 0.2612 0.03410 0.02800 -0.0902 0.0322 0.0156
-1.500 0.3031 0.03208 0.02579 -0.0928 0.0331 0.0158
-1.250 0.3410 0.03011 0.02370 -0.0946 0.0356 0.0158
-1.000 0.3685 0.02882 0.02239 -0.0960 0.0383 0.0161
-0.750 0.4009 0.02762 0.02116 -0.0971 0.0416 0.0165
-0.500 0.4347 0.02648 0.01995 -0.0980 0.0474 0.0170
3.250 0.8828 0.02722 0.01929 -0.0963 0.0228 0.0361
3.500 0.9099 0.02817 0.02037 -0.0957 0.0221 0.0314
3.750 0.9361 0.02939 0.02168 -0.0954 0.0216 0.0287
4.000 0.9611 0.03102 0.02336 -0.0950 0.0213 0.0274
4.250 0.9855 0.03335 0.02567 -0.0948 0.0210 0.0270
4.500 1.0088 0.03653 0.02891 -0.0943 0.0208 0.0274
4.750 1.0347 0.03666 0.02970 -0.0919 0.0201 0.0295
5.000 1.0553 0.03714 0.03194 -0.0906 0.0196 1.0000
5.250 1.0772 0.03934 0.03430 -0.0895 0.0191 1.0000
5.500 1.0977 0.04164 0.03674 -0.0885 0.0187 1.0000
5.750 1.1168 0.04404 0.03927 -0.0875 0.0184 1.0000
6.000 1.1345 0.04658 0.04192 -0.0865 0.0182 1.0000
6.250 1.1509 0.04930 0.04475 -0.0856 0.0181 1.0000
6.500 1.1658 0.05221 0.04776 -0.0847 0.0179 1.0000
6.750 1.1795 0.05543 0.05104 -0.0839 0.0178 1.0000
7.000 1.1923 0.05930 0.05493 -0.0832 0.0177 1.0000
7.250 1.2033 0.06389 0.05957 -0.0824 0.0177 1.0000
7.500 1.2075 0.06738 0.06339 -0.0804 0.0176 1.0000
7.750 1.2084 0.07109 0.06743 -0.0782 0.0176 1.0000
8.000 1.2026 0.07550 0.07228 -0.0755 0.0174 1.0000
8.250 1.1941 0.08069 0.07780 -0.0738 0.0170 1.0000
8.500 1.1805 0.08517 0.08244 -0.0725 0.0169 1.0000
8.750 1.1584 0.08955 0.08693 -0.0715 0.0169 1.0000
9.000 1.1356 0.09527 0.09276 -0.0736 0.0170 1.0000
9.250 1.1140 0.10274 0.10033 -0.0787 0.0171 1.0000
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