XFOIL Version 6.94 Calculated polar for: K3311 (smoothed) 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 0.3684 0.00671 0.00209 -0.0757 0.6788 0.9212 0.500 0.4742 0.00682 0.00205 -0.0866 0.6576 0.9919 1.000 0.5327 0.00699 0.00206 -0.0873 0.6379 1.0000 1.500 0.5813 0.00717 0.00210 -0.0858 0.6191 1.0000 2.000 0.6305 0.00738 0.00220 -0.0844 0.6004 1.0000 2.500 0.6799 0.00761 0.00232 -0.0830 0.5816 1.0000 3.000 0.7293 0.00786 0.00249 -0.0816 0.5625 1.0000 3.500 0.7790 0.00809 0.00269 -0.0803 0.5428 1.0000 4.000 0.8286 0.00835 0.00293 -0.0790 0.5224 1.0000 4.500 0.8777 0.00865 0.00319 -0.0776 0.5005 1.0000 5.000 0.9263 0.00899 0.00351 -0.0762 0.4776 1.0000 5.500 0.9748 0.00933 0.00385 -0.0748 0.4523 1.0000 6.000 1.0221 0.00975 0.00426 -0.0731 0.4240 1.0000 6.500 1.0654 0.01033 0.00471 -0.0709 0.3780 1.0000 7.000 1.1072 0.01106 0.00529 -0.0684 0.3283 1.0000 7.500 1.1453 0.01204 0.00606 -0.0655 0.2692 1.0000 8.000 1.1788 0.01330 0.00703 -0.0619 0.2043 1.0000 8.500 1.2066 0.01485 0.00824 -0.0576 0.1381 1.0000 9.000 1.2208 0.01694 0.00990 -0.0512 0.0650 1.0000 9.500 1.2308 0.01897 0.01177 -0.0440 0.0346 1.0000 10.000 1.2465 0.02084 0.01376 -0.0383 0.0264 1.0000 10.500 1.2490 0.02370 0.01677 -0.0318 0.0220 1.0000 11.000 1.2649 0.02602 0.01929 -0.0278 0.0200 1.0000 11.500 1.2767 0.02888 0.02230 -0.0243 0.0179 1.0000 12.000 1.2737 0.03334 0.02694 -0.0207 0.0165 1.0000 12.500 1.2696 0.03841 0.03225 -0.0179 0.0155 1.0000 13.000 1.2785 0.04255 0.03660 -0.0164 0.0145 1.0000 13.500 1.2834 0.04728 0.04154 -0.0152 0.0136 1.0000 14.000 1.2863 0.05246 0.04692 -0.0146 0.0127 1.0000 14.500 1.2862 0.05821 0.05285 -0.0145 0.0121 1.0000 15.000 1.2750 0.06553 0.06040 -0.0138 0.0112 1.0000 15.500 1.2671 0.07311 0.06830 -0.0149 0.0108 1.0000 16.000 1.2577 0.08143 0.07693 -0.0171 0.0105 1.0000 16.500 1.2435 0.09093 0.08675 -0.0203 0.0103 1.0000 17.000 1.2216 0.10237 0.09854 -0.0250 0.0102 1.0000 17.500 1.1958 0.11531 0.11181 -0.0313 0.0101 1.0000 18.000 1.1648 0.13034 0.12717 -0.0395 0.0101 1.0000 18.500 1.1304 0.14737 0.14452 -0.0496 0.0101 1.0000 19.000 1.0858 0.16869 0.16614 -0.0627 0.0105 1.0000