XFOIL Version 6.94 Calculated polar for: Eiffel 430 (Lachassgne) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.750 -0.3519 0.05484 0.04917 0.0308 0.9405 0.6720 -2.500 -0.1473 0.05275 0.04463 -0.0302 0.9259 0.3289 -2.250 -0.1174 0.05099 0.04245 -0.0320 0.9200 0.3062 -2.000 -0.0784 0.04945 0.04036 -0.0348 0.9129 0.2875 -1.750 -0.0351 0.04756 0.03808 -0.0378 0.9059 0.2779 -1.500 -0.0088 0.04627 0.03649 -0.0378 0.8977 0.2797 -1.250 0.0355 0.04506 0.03480 -0.0405 0.8887 0.2877 -1.000 0.0639 0.04389 0.03334 -0.0407 0.8825 0.2938 -0.750 0.1001 0.04293 0.03201 -0.0422 0.8756 0.3139 -0.500 0.1608 0.04162 0.03035 -0.0475 0.8680 0.3545 -0.250 0.1993 0.04049 0.02933 -0.0495 0.8584 0.4061 0.000 0.2598 0.03931 0.02847 -0.0548 0.8483 0.4772 0.250 0.2891 0.03857 0.02824 -0.0551 0.8362 0.5341 0.500 0.3883 0.03740 0.02777 -0.0672 0.8173 1.0000 0.750 0.4327 0.03750 0.02746 -0.0689 0.7981 1.0000 1.000 0.4743 0.03756 0.02724 -0.0702 0.7791 1.0000 1.250 0.5155 0.03755 0.02701 -0.0713 0.7589 1.0000 1.500 0.5574 0.03746 0.02677 -0.0724 0.7377 1.0000 1.750 0.5993 0.03736 0.02654 -0.0734 0.7159 1.0000 2.000 0.6372 0.03742 0.02649 -0.0739 0.6946 1.0000 2.250 0.6702 0.03780 0.02677 -0.0739 0.6745 1.0000 2.500 0.6986 0.03848 0.02735 -0.0735 0.6564 1.0000 2.750 0.7411 0.03846 0.02723 -0.0745 0.6432 1.0000 3.000 0.7517 0.04019 0.02891 -0.0727 0.6276 1.0000 3.250 0.7509 0.04279 0.03149 -0.0703 0.6149 1.0000 3.500 0.7740 0.04412 0.03279 -0.0699 0.6062 1.0000 3.750 0.7633 0.04758 0.03623 -0.0673 0.5972 1.0000 4.000 0.7545 0.05085 0.03948 -0.0648 0.5887 1.0000 4.250 0.7872 0.05146 0.04009 -0.0648 0.5798 1.0000 4.500 0.7372 0.05765 0.04621 -0.0608 0.5735 1.0000 4.750 0.7498 0.05966 0.04823 -0.0599 0.5653 1.0000 5.000 0.7529 0.06222 0.05077 -0.0585 0.5562 1.0000