XFOIL Version 6.94 Calculated polar for: E201 (11.88%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3456 0.00871 0.00319 -0.0754 0.6844 0.8554 0.500 0.4137 0.00874 0.00327 -0.0772 0.6723 0.9507 1.000 0.5093 0.00886 0.00325 -0.0857 0.6603 0.9957 1.500 0.5633 0.00903 0.00332 -0.0857 0.6483 1.0000 2.000 0.6115 0.00926 0.00349 -0.0843 0.6363 1.0000 2.500 0.6615 0.00952 0.00370 -0.0832 0.6249 1.0000 3.500 0.7635 0.00997 0.00411 -0.0813 0.5980 1.0000 4.000 0.8146 0.01018 0.00433 -0.0803 0.5824 1.0000 4.500 0.8656 0.01038 0.00459 -0.0793 0.5661 1.0000 5.000 0.9164 0.01058 0.00482 -0.0782 0.5481 1.0000 5.500 0.9665 0.01080 0.00508 -0.0770 0.5279 1.0000 6.000 1.0148 0.01099 0.00541 -0.0755 0.5015 1.0000 6.500 1.0590 0.01128 0.00567 -0.0731 0.4569 1.0000 7.000 1.0989 0.01193 0.00619 -0.0702 0.3922 1.0000 7.500 1.1235 0.01357 0.00724 -0.0652 0.2743 1.0000 8.000 1.1424 0.01569 0.00880 -0.0598 0.1723 1.0000 8.500 1.1594 0.01768 0.01044 -0.0541 0.1027 1.0000 9.000 1.1563 0.02050 0.01278 -0.0456 0.0346 1.0000 9.500 1.1606 0.02327 0.01557 -0.0390 0.0217 1.0000 10.000 1.1742 0.02575 0.01823 -0.0346 0.0186 1.0000 10.500 1.1830 0.02887 0.02152 -0.0307 0.0170 1.0000 11.000 1.1843 0.03301 0.02583 -0.0272 0.0160 1.0000 11.500 1.1861 0.03758 0.03061 -0.0242 0.0153 1.0000 12.000 1.1973 0.04162 0.03486 -0.0219 0.0149 1.0000 12.500 1.2114 0.04576 0.03923 -0.0199 0.0145 1.0000 13.000 1.2268 0.05019 0.04394 -0.0180 0.0143 1.0000 13.500 1.2374 0.05539 0.04948 -0.0166 0.0139 1.0000 14.000 1.2395 0.06185 0.05637 -0.0158 0.0139 1.0000 14.500 1.2328 0.06893 0.06381 -0.0164 0.0134 1.0000 15.000 1.2161 0.07809 0.07339 -0.0183 0.0133 1.0000 15.500 1.1887 0.08956 0.08532 -0.0221 0.0134 1.0000 16.000 1.1524 0.10375 0.09996 -0.0286 0.0138 1.0000 16.500 1.1127 0.12017 0.11677 -0.0377 0.0141 1.0000 17.000 1.0696 0.13967 0.13661 -0.0499 0.0144 1.0000 17.500 1.0184 0.16459 0.16176 -0.0655 0.0151 1.0000