XFOIL Version 6.94 Calculated polar for: K3311 (original) 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 ------- -------- --------- --------- -------- ------- ------- 1.000 0.5317 0.00706 0.00211 -0.0866 0.6368 1.0000 1.500 0.5807 0.00723 0.00215 -0.0851 0.6181 1.0000 2.000 0.6299 0.00735 0.00220 -0.0837 0.5950 1.0000 2.500 0.6793 0.00755 0.00231 -0.0823 0.5750 1.0000 3.000 0.7290 0.00780 0.00247 -0.0810 0.5561 1.0000 3.500 0.7788 0.00809 0.00270 -0.0797 0.5376 1.0000 4.000 0.8281 0.00842 0.00294 -0.0784 0.5167 1.0000 4.500 0.8779 0.00870 0.00324 -0.0772 0.4954 1.0000 5.000 0.9269 0.00903 0.00355 -0.0758 0.4715 1.0000 5.500 0.9753 0.00942 0.00393 -0.0744 0.4473 1.0000 6.000 1.0225 0.00981 0.00431 -0.0728 0.4122 1.0000 6.500 1.0656 0.01044 0.00480 -0.0705 0.3590 1.0000 7.000 1.1038 0.01145 0.00552 -0.0675 0.2963 1.0000 7.500 1.1384 0.01271 0.00643 -0.0642 0.2178 1.0000 8.000 1.1625 0.01464 0.00781 -0.0593 0.1197 1.0000 8.500 1.1686 0.01745 0.00998 -0.0516 0.0288 1.0000 9.000 1.1877 0.01903 0.01166 -0.0456 0.0211 1.0000 9.500 1.2020 0.02098 0.01380 -0.0395 0.0183 1.0000 10.000 1.2166 0.02306 0.01608 -0.0343 0.0165 1.0000 10.500 1.2271 0.02563 0.01881 -0.0295 0.0152 1.0000 11.000 1.2192 0.02999 0.02337 -0.0242 0.0136 1.0000 11.500 1.2245 0.03388 0.02746 -0.0209 0.0131 1.0000 12.000 1.2344 0.03770 0.03149 -0.0184 0.0125 1.0000 12.500 1.2431 0.04188 0.03588 -0.0163 0.0119 1.0000 13.000 1.2513 0.04642 0.04067 -0.0143 0.0116 1.0000 13.500 1.2579 0.05137 0.04587 -0.0128 0.0112 1.0000 14.000 1.2603 0.05693 0.05169 -0.0120 0.0107 1.0000 14.500 1.2570 0.06363 0.05872 -0.0117 0.0107 1.0000 15.000 1.2484 0.07105 0.06641 -0.0129 0.0103 1.0000 15.500 1.2388 0.07895 0.07447 -0.0152 0.0096 1.0000 16.000 1.2195 0.08911 0.08497 -0.0186 0.0095 1.0000 16.500 1.1951 0.10096 0.09716 -0.0237 0.0095 1.0000 17.000 1.1627 0.11553 0.11214 -0.0313 0.0098 1.0000 17.500 1.0985 0.13942 0.13662 -0.0453 0.0106 1.0000 18.000 1.0112 0.17528 0.17292 -0.0670 0.0121 1.0000