XFOIL Version 6.94 Calculated polar for: E203 (13.64%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3502 0.00859 0.00243 -0.0821 0.6518 0.5868 0.500 0.4059 0.00863 0.00249 -0.0821 0.6406 0.6079 1.000 0.4615 0.00866 0.00256 -0.0820 0.6297 0.6313 1.500 0.5166 0.00866 0.00269 -0.0819 0.6184 0.6600 2.000 0.5714 0.00870 0.00284 -0.0817 0.6078 0.6968 2.500 0.6249 0.00868 0.00301 -0.0811 0.5964 0.7470 3.000 0.6756 0.00860 0.00321 -0.0798 0.5831 0.8148 3.500 0.7220 0.00852 0.00341 -0.0773 0.5700 0.9088 4.000 0.7983 0.00858 0.00354 -0.0816 0.5540 1.0000 4.500 0.8494 0.00878 0.00374 -0.0807 0.5379 1.0000 5.000 0.9005 0.00898 0.00395 -0.0799 0.5199 1.0000 5.500 0.9508 0.00922 0.00421 -0.0788 0.4984 1.0000 6.000 1.0000 0.00951 0.00451 -0.0776 0.4726 1.0000 6.500 1.0466 0.00991 0.00487 -0.0759 0.4350 1.0000 7.000 1.0857 0.01069 0.00542 -0.0729 0.3669 1.0000 7.500 1.1115 0.01228 0.00646 -0.0681 0.2614 1.0000 8.000 1.1340 0.01404 0.00774 -0.0629 0.1735 1.0000 8.500 1.1529 0.01562 0.00902 -0.0571 0.1162 1.0000 9.000 1.1732 0.01707 0.01033 -0.0517 0.0806 1.0000 9.500 1.1885 0.01887 0.01197 -0.0460 0.0492 1.0000 10.000 1.1914 0.02155 0.01444 -0.0395 0.0200 1.0000 10.500 1.2027 0.02408 0.01706 -0.0348 0.0149 1.0000 11.000 1.2118 0.02708 0.02026 -0.0307 0.0132 1.0000 11.500 1.2223 0.03029 0.02365 -0.0277 0.0119 1.0000 12.000 1.2295 0.03409 0.02761 -0.0251 0.0112 1.0000 12.500 1.2316 0.03865 0.03234 -0.0231 0.0106 1.0000 13.000 1.2256 0.04432 0.03821 -0.0213 0.0101 1.0000 13.500 1.2225 0.05006 0.04416 -0.0200 0.0098 1.0000 14.000 1.2275 0.05528 0.04961 -0.0193 0.0097 1.0000 14.500 1.2332 0.06071 0.05528 -0.0192 0.0095 1.0000 15.000 1.2359 0.06682 0.06165 -0.0196 0.0092 1.0000 15.500 1.2356 0.07365 0.06875 -0.0207 0.0089 1.0000 16.000 1.2316 0.08141 0.07679 -0.0227 0.0086 1.0000 16.500 1.2212 0.09058 0.08628 -0.0256 0.0085 1.0000 17.000 1.2056 0.10121 0.09724 -0.0299 0.0085 1.0000 17.500 1.1833 0.11371 0.11010 -0.0358 0.0086 1.0000 18.000 1.1541 0.12854 0.12530 -0.0440 0.0086 1.0000 18.500 1.1205 0.14555 0.14266 -0.0543 0.0088 1.0000 19.000 1.0781 0.16655 0.16400 -0.0676 0.0090 1.0000 19.500 0.9969 0.20356 0.20133 -0.0890 0.0099 1.0000 21.000 0.7650 0.24735 0.24562 -0.1102 0.0164 1.0000 21.500 0.7739 0.25539 0.25367 -0.1138 0.0155 1.0000 22.000 0.7834 0.26298 0.26127 -0.1172 0.0149 1.0000 24.000 0.8132 0.29991 0.29826 -0.1321 0.0121 1.0000 24.500 0.8213 0.30844 0.30681 -0.1356 0.0113 1.0000 25.000 0.8296 0.31642 0.31481 -0.1389 0.0106 1.0000 25.500 0.8395 0.32344 0.32185 -0.1415 0.0101 1.0000 26.000 0.8483 0.33316 0.33158 -0.1443 0.0099 1.0000 26.500 0.8517 0.34352 0.34195 -0.1486 0.0097 1.0000 27.000 0.8569 0.35409 0.35254 -0.1527 0.0091 1.0000