XFOIL Version 6.94 Calculated polar for: GOEN 611 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.2242 0.06386 0.05590 -0.0083 1.0002 0.4421 -2.750 -0.1759 0.05985 0.05159 -0.0201 1.0002 0.3962 -2.500 -0.1258 0.05653 0.04779 -0.0309 1.0002 0.3587 -2.250 -0.0886 0.05388 0.04483 -0.0361 1.0002 0.3358 -2.000 -0.0517 0.05180 0.04234 -0.0407 1.0002 0.3171 -1.750 -0.0246 0.05001 0.04040 -0.0421 1.0002 0.3079 -1.500 0.0068 0.04886 0.03881 -0.0446 1.0002 0.3000 -1.250 0.0326 0.04805 0.03767 -0.0457 1.0002 0.2968 -1.000 0.0560 0.04742 0.03684 -0.0462 1.0002 0.2949 -0.750 0.0787 0.04716 0.03636 -0.0468 1.0002 0.2927 -0.500 0.1004 0.04724 0.03624 -0.0473 1.0002 0.2910 -0.250 0.1214 0.04770 0.03651 -0.0480 1.0002 0.2906 0.000 0.1398 0.04854 0.03721 -0.0487 1.0002 0.2926 0.250 0.1556 0.04981 0.03836 -0.0495 1.0002 0.2964 0.500 0.1691 0.05129 0.03989 -0.0504 1.0002 0.3013 0.750 0.1809 0.05310 0.04178 -0.0516 1.0002 0.3072 1.000 0.1919 0.05524 0.04398 -0.0530 1.0002 0.3133 1.250 0.2999 0.05546 0.04460 -0.0703 0.9528 0.3553 1.500 0.4407 0.05112 0.04160 -0.0857 0.8563 0.9998 1.750 0.6031 0.04481 0.03349 -0.0916 0.7277 0.9998 2.000 0.6367 0.04480 0.03287 -0.0866 0.6594 0.9998 2.250 0.6645 0.04562 0.03310 -0.0822 0.6057 0.9998 2.500 0.6886 0.04725 0.03426 -0.0792 0.5636 0.9998 2.750 0.7097 0.04946 0.03623 -0.0776 0.5287 0.9998 3.000 0.7344 0.05125 0.03763 -0.0758 0.5026 0.9998 3.250 0.7591 0.05379 0.03997 -0.0756 0.4834 0.9998 3.500 0.7747 0.05808 0.04445 -0.0773 0.4699 0.9998 3.750 0.7945 0.06157 0.04787 -0.0778 0.4601 0.9998 4.000 0.8011 0.06663 0.05310 -0.0793 0.4526 0.9998 4.250 0.8263 0.06901 0.05524 -0.0786 0.4427 0.9998 4.500 0.8178 0.07546 0.06192 -0.0803 0.4394 0.9998 4.750 0.8065 0.08189 0.06845 -0.0815 0.4380 0.9998 5.000 0.7949 0.08825 0.07487 -0.0827 0.4389 0.9998