XFOIL Version 6.96 Calculated polar for: WORTMANN FX 77-080 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.6290 0.09078 0.08857 -0.0048 1.0000 0.0176 -12.000 -0.9149 0.06235 0.05974 -0.0192 1.0000 0.0146 -11.750 -0.9382 0.05360 0.05078 -0.0278 1.0000 0.0145 -11.500 -0.9700 0.04669 0.04359 -0.0315 1.0000 0.0140 -11.250 -0.9861 0.04320 0.03989 -0.0304 1.0000 0.0142 -11.000 -1.0004 0.03988 0.03631 -0.0276 1.0000 0.0142 -10.750 -1.0039 0.03692 0.03307 -0.0254 1.0000 0.0144 -10.500 -1.0040 0.03392 0.02975 -0.0232 1.0000 0.0145 -10.250 -0.9990 0.03129 0.02682 -0.0210 1.0000 0.0147 -10.000 -0.9901 0.02899 0.02422 -0.0190 1.0000 0.0150 -9.750 -0.9768 0.02723 0.02221 -0.0173 1.0000 0.0152 -9.500 -0.9606 0.02591 0.02066 -0.0157 1.0000 0.0156 -9.250 -0.9483 0.02357 0.01804 -0.0138 1.0000 0.0159 -9.000 -0.9352 0.02136 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0.8747 0.9484 0.750 0.1243 0.00538 0.00184 -0.0075 0.8374 0.9598 1.000 0.1691 0.00565 0.00192 -0.0106 0.7831 0.9661 1.250 0.2024 0.00598 0.00198 -0.0114 0.7110 0.9736 1.500 0.2380 0.00634 0.00203 -0.0128 0.6343 0.9791 1.750 0.2725 0.00674 0.00211 -0.0142 0.5513 0.9847 2.000 0.3083 0.00718 0.00219 -0.0160 0.4608 0.9903 2.250 0.3452 0.00760 0.00225 -0.0181 0.3738 0.9943 2.500 0.3813 0.00800 0.00234 -0.0201 0.2967 0.9984 2.750 0.4099 0.00832 0.00242 -0.0206 0.2413 1.0000 3.000 0.4308 0.00854 0.00250 -0.0193 0.2094 1.0000 3.250 0.4522 0.00874 0.00261 -0.0180 0.1874 1.0000 3.500 0.4738 0.00893 0.00274 -0.0167 0.1706 1.0000 3.750 0.4955 0.00913 0.00288 -0.0155 0.1553 1.0000 4.000 0.5175 0.00931 0.00303 -0.0143 0.1419 1.0000 4.250 0.5396 0.00951 0.00319 -0.0131 0.1278 1.0000 4.500 0.5616 0.00974 0.00337 -0.0119 0.1112 1.0000 4.750 0.5836 0.00999 0.00358 -0.0107 0.0917 1.0000 5.000 0.6047 0.01039 0.00385 -0.0094 0.0686 1.0000 5.250 0.6259 0.01082 0.00422 -0.0080 0.0544 1.0000 5.500 0.6467 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1.0051 0.03377 0.02959 0.0231 0.0144 1.0000 10.750 1.0054 0.03675 0.03287 0.0253 0.0144 1.0000 11.000 1.0023 0.03968 0.03609 0.0275 0.0140 1.0000 11.250 0.9868 0.04315 0.03984 0.0303 0.0139 1.0000 11.500 0.9624 0.04771 0.04466 0.0311 0.0143 1.0000 11.750 0.9463 0.05246 0.04961 0.0284 0.0140 1.0000 12.000 0.9131 0.06319 0.06060 0.0180 0.0144 1.0000