XFOIL Version 6.94 Calculated polar for: E195 (11.82%) 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 0.3222 0.00734 0.00240 -0.0659 0.6431 0.8920 0.500 0.4009 0.00743 0.00246 -0.0703 0.6328 0.9674 1.000 0.4897 0.00755 0.00249 -0.0774 0.6226 0.9928 1.500 0.5587 0.00769 0.00250 -0.0805 0.6129 1.0000 2.000 0.6070 0.00779 0.00260 -0.0791 0.6027 1.0000 2.500 0.6565 0.00798 0.00273 -0.0778 0.5927 1.0000 3.000 0.7062 0.00814 0.00285 -0.0766 0.5811 1.0000 3.500 0.7559 0.00828 0.00303 -0.0754 0.5679 1.0000 4.000 0.8059 0.00845 0.00321 -0.0742 0.5542 1.0000 4.500 0.8560 0.00862 0.00340 -0.0730 0.5390 1.0000 5.000 0.9062 0.00880 0.00363 -0.0719 0.5219 1.0000 5.500 0.9563 0.00902 0.00388 -0.0707 0.5026 1.0000 6.000 1.0042 0.00928 0.00415 -0.0692 0.4702 1.0000 6.500 1.0474 0.00983 0.00452 -0.0670 0.4113 1.0000 7.000 1.0856 0.01083 0.00523 -0.0641 0.3318 1.0000 7.500 1.1118 0.01265 0.00647 -0.0596 0.2202 1.0000 8.000 1.1352 0.01455 0.00788 -0.0549 0.1301 1.0000 8.500 1.1521 0.01654 0.00944 -0.0491 0.0610 1.0000 9.000 1.1555 0.01875 0.01139 -0.0413 0.0194 1.0000 9.500 1.1717 0.02060 0.01335 -0.0360 0.0145 1.0000 10.000 1.1858 0.02282 0.01570 -0.0313 0.0127 1.0000 10.500 1.1887 0.02615 0.01923 -0.0266 0.0117 1.0000 11.000 1.1974 0.02948 0.02276 -0.0234 0.0114 1.0000 11.500 1.2044 0.03329 0.02679 -0.0207 0.0110 1.0000 12.000 1.2103 0.03747 0.03115 -0.0185 0.0106 1.0000 12.500 1.2186 0.04161 0.03547 -0.0170 0.0100 1.0000 13.000 1.2253 0.04612 0.04017 -0.0156 0.0096 1.0000 13.500 1.2310 0.05097 0.04522 -0.0144 0.0094 1.0000 14.000 1.2374 0.05606 0.05056 -0.0134 0.0094 1.0000 14.500 1.2411 0.06173 0.05649 -0.0132 0.0091 1.0000 15.000 1.2407 0.06834 0.06342 -0.0134 0.0091 1.0000 15.500 1.2343 0.07606 0.07143 -0.0148 0.0089 1.0000 16.000 1.2191 0.08571 0.08148 -0.0174 0.0090 1.0000 16.500 1.1978 0.09703 0.09316 -0.0218 0.0090 1.0000 17.000 1.1626 0.11198 0.10858 -0.0288 0.0093 1.0000 17.500 1.1198 0.13018 0.12722 -0.0392 0.0096 1.0000 18.000 1.0680 0.15310 0.15054 -0.0534 0.0100 1.0000 18.500 0.9773 0.19451 0.19222 -0.0766 0.0114 1.0000