XFOIL Version 6.94 Calculated polar for: HOBIE 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 0.4592 0.00800 0.00162 -0.1017 0.7163 0.2790 0.500 0.5124 0.00780 0.00169 -0.1010 0.6919 0.3962 1.000 0.5611 0.00713 0.00183 -0.0995 0.6650 0.7004 1.500 0.6221 0.00672 0.00186 -0.1001 0.6316 1.0000 2.000 0.6741 0.00701 0.00194 -0.0991 0.5881 1.0000 2.500 0.7258 0.00738 0.00211 -0.0980 0.5482 1.0000 3.000 0.7773 0.00779 0.00235 -0.0970 0.5089 1.0000 3.500 0.8292 0.00819 0.00263 -0.0961 0.4754 1.0000 4.000 0.8806 0.00863 0.00297 -0.0952 0.4439 1.0000 4.500 0.9320 0.00910 0.00338 -0.0942 0.4165 1.0000 5.000 0.9821 0.00964 0.00381 -0.0931 0.3694 1.0000 5.500 1.0259 0.01077 0.00444 -0.0912 0.2561 1.0000 6.000 1.0690 0.01205 0.00542 -0.0892 0.2030 1.0000 6.500 1.1065 0.01392 0.00665 -0.0866 0.0756 1.0000 7.000 1.1473 0.01541 0.00806 -0.0841 0.0432 1.0000 7.500 1.1864 0.01697 0.00957 -0.0814 0.0267 1.0000 8.000 1.2234 0.01856 0.01127 -0.0784 0.0211 1.0000 8.500 1.2541 0.02052 0.01342 -0.0744 0.0182 1.0000 9.000 1.2788 0.02269 0.01569 -0.0699 0.0161 1.0000 9.500 1.2947 0.02518 0.01838 -0.0640 0.0146 1.0000 10.000 1.3136 0.02764 0.02104 -0.0591 0.0135 1.0000 10.500 1.3315 0.03046 0.02401 -0.0547 0.0126 1.0000 11.000 1.3512 0.03566 0.02942 -0.0512 0.0118 1.0000 11.500 1.3626 0.03910 0.03327 -0.0471 0.0113 1.0000 12.000 1.3686 0.04380 0.03841 -0.0436 0.0108 1.0000 12.500 1.3647 0.04968 0.04473 -0.0406 0.0103 1.0000 13.000 1.3481 0.05758 0.05312 -0.0389 0.0102 1.0000 13.500 1.3199 0.06742 0.06345 -0.0394 0.0102 1.0000 14.000 1.2795 0.08023 0.07675 -0.0431 0.0104 1.0000 14.500 1.2374 0.09505 0.09199 -0.0501 0.0106 1.0000 15.000 1.1948 0.11237 0.10966 -0.0604 0.0108 1.0000 15.500 1.1539 0.13189 0.12946 -0.0731 0.0111 1.0000 16.000 1.1161 0.15356 0.15131 -0.0875 0.0116 1.0000