XFOIL Version 6.94 Calculated polar for: E193 (10.22%) 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 0.4176 0.00690 0.00206 -0.0857 0.6527 1.0000 0.500 0.4676 0.00706 0.00206 -0.0846 0.6414 1.0000 1.000 0.5182 0.00722 0.00209 -0.0835 0.6302 1.0000 1.500 0.5694 0.00737 0.00219 -0.0825 0.6190 1.0000 2.000 0.6208 0.00757 0.00232 -0.0816 0.6081 1.0000 2.500 0.6724 0.00777 0.00244 -0.0807 0.5960 1.0000 3.000 0.7241 0.00792 0.00260 -0.0798 0.5824 1.0000 3.500 0.7760 0.00809 0.00277 -0.0789 0.5678 1.0000 4.000 0.8279 0.00827 0.00297 -0.0781 0.5519 1.0000 4.500 0.8797 0.00847 0.00319 -0.0773 0.5349 1.0000 5.000 0.9310 0.00869 0.00345 -0.0763 0.5149 1.0000 5.500 0.9802 0.00895 0.00368 -0.0750 0.4802 1.0000 6.000 1.0273 0.00940 0.00404 -0.0734 0.4296 1.0000 6.500 1.0676 0.01041 0.00467 -0.0709 0.3348 1.0000 7.000 1.0985 0.01226 0.00590 -0.0672 0.2113 1.0000 7.500 1.1265 0.01427 0.00733 -0.0633 0.1083 1.0000 8.000 1.1443 0.01681 0.00928 -0.0577 0.0218 1.0000 8.500 1.1739 0.01830 0.01086 -0.0537 0.0156 1.0000 9.000 1.1962 0.01978 0.01249 -0.0485 0.0140 1.0000 9.500 1.2123 0.02168 0.01456 -0.0430 0.0131 1.0000 10.000 1.2159 0.02462 0.01768 -0.0370 0.0123 1.0000 10.500 1.2189 0.02814 0.02143 -0.0322 0.0119 1.0000 11.000 1.2283 0.03166 0.02515 -0.0289 0.0117 1.0000 11.500 1.2396 0.03542 0.02912 -0.0260 0.0116 1.0000 12.000 1.2540 0.03915 0.03307 -0.0238 0.0112 1.0000 12.500 1.2677 0.04323 0.03739 -0.0218 0.0109 1.0000 13.000 1.2787 0.04805 0.04254 -0.0199 0.0108 1.0000 13.500 1.2833 0.05382 0.04867 -0.0185 0.0109 1.0000 14.000 1.2769 0.06105 0.05631 -0.0180 0.0109 1.0000 14.500 1.2595 0.06988 0.06556 -0.0189 0.0110 1.0000 15.000 1.2350 0.08027 0.07635 -0.0217 0.0112 1.0000 15.500 1.2015 0.09314 0.08963 -0.0268 0.0114 1.0000 16.000 1.1664 0.10769 0.10453 -0.0341 0.0115 1.0000 16.500 1.1261 0.12512 0.12228 -0.0441 0.0117 1.0000 17.000 1.1078 0.13903 0.13639 -0.0521 0.0123 1.0000