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 = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3513 0.00881 0.00339 -0.0717 0.6720 0.9627 0.500 0.4479 0.00896 0.00333 -0.0803 0.6617 0.9939 1.000 0.5093 0.00905 0.00333 -0.0820 0.6505 1.0000 1.500 0.5567 0.00925 0.00346 -0.0805 0.6402 1.0000 2.000 0.6060 0.00948 0.00357 -0.0793 0.6304 1.0000 2.500 0.6549 0.00969 0.00381 -0.0780 0.6192 1.0000 3.000 0.7049 0.00994 0.00403 -0.0769 0.6083 1.0000 3.500 0.7555 0.01016 0.00421 -0.0758 0.5963 1.0000 4.000 0.8051 0.01033 0.00442 -0.0745 0.5820 1.0000 4.500 0.8551 0.01051 0.00465 -0.0733 0.5671 1.0000 5.000 0.9051 0.01068 0.00489 -0.0721 0.5507 1.0000 5.500 0.9548 0.01084 0.00511 -0.0708 0.5321 1.0000 6.000 1.0039 0.01104 0.00541 -0.0694 0.5116 1.0000 6.500 1.0496 0.01123 0.00565 -0.0674 0.4772 1.0000 7.000 1.0903 0.01169 0.00603 -0.0645 0.4177 1.0000 7.500 1.1217 0.01285 0.00683 -0.0605 0.3248 1.0000 8.000 1.1406 0.01488 0.00829 -0.0550 0.2184 1.0000 8.500 1.1554 0.01703 0.00998 -0.0491 0.1335 1.0000 9.000 1.1602 0.01924 0.01185 -0.0417 0.0715 1.0000 9.500 1.1525 0.02250 0.01476 -0.0338 0.0252 1.0000 10.000 1.1610 0.02529 0.01772 -0.0290 0.0196 1.0000 10.500 1.1672 0.02865 0.02123 -0.0251 0.0172 1.0000 11.000 1.1656 0.03307 0.02584 -0.0217 0.0162 1.0000 11.500 1.1729 0.03708 0.03008 -0.0193 0.0155 1.0000 12.000 1.1800 0.04135 0.03454 -0.0172 0.0150 1.0000 12.500 1.1902 0.04559 0.03898 -0.0152 0.0146 1.0000 13.000 1.2030 0.04980 0.04341 -0.0135 0.0140 1.0000 13.500 1.2140 0.05438 0.04821 -0.0124 0.0133 1.0000 14.000 1.2233 0.05954 0.05366 -0.0114 0.0131 1.0000 14.500 1.2265 0.06547 0.05986 -0.0114 0.0126 1.0000 15.000 1.2212 0.07305 0.06785 -0.0120 0.0126 1.0000 15.500 1.2073 0.08208 0.07728 -0.0140 0.0126 1.0000 16.000 1.1800 0.09401 0.08971 -0.0182 0.0128 1.0000 16.500 1.1440 0.10851 0.10468 -0.0250 0.0131 1.0000 17.000 1.0873 0.12944 0.12615 -0.0372 0.0137 1.0000 17.500 1.0290 0.15467 0.15175 -0.0531 0.0144 1.0000 18.000 0.9624 0.19037 0.18759 -0.0721 0.0172 1.0000 19.500 0.7492 0.21782 0.21552 -0.0861 0.0306 1.0000 20.000 0.7465 0.22736 0.22506 -0.0927 0.0276 1.0000 20.500 0.7548 0.23531 0.23303 -0.0964 0.0254 1.0000 21.000 0.7653 0.24247 0.24023 -0.0995 0.0240 1.0000 21.500 0.7812 0.24908 0.24689 -0.1011 0.0229 1.0000 22.000 0.7883 0.26006 0.25786 -0.1047 0.0223 1.0000 22.500 0.7883 0.26877 0.26658 -0.1104 0.0216 1.0000 23.000 0.7947 0.27779 0.27562 -0.1147 0.0195 1.0000 23.500 0.8034 0.28565 0.28350 -0.1180 0.0178 1.0000 24.000 0.8143 0.29270 0.29060 -0.1207 0.0168 1.0000 24.500 0.8258 0.30279 0.30071 -0.1229 0.0163 1.0000 25.000 0.8268 0.31198 0.30991 -0.1281 0.0159 1.0000 25.500 0.8329 0.32162 0.31957 -0.1323 0.0144 1.0000 26.000 0.8402 0.33034 0.32832 -0.1357 0.0135 1.0000 26.500 0.8476 0.33867 0.33668 -0.1389 0.0124 1.0000 27.000 0.8561 0.34674 0.34478 -0.1415 0.0119 1.0000 27.500 0.8643 0.35714 0.35521 -0.1443 0.0117 1.0000 28.000 0.8675 0.36651 0.36461 -0.1484 0.0116 1.0000 28.500 0.8719 0.37645 0.37456 -0.1526 0.0110 1.0000 29.000 0.8775 0.38602 0.38416 -0.1559 0.0099 1.0000 29.500 0.8830 0.39531 0.39348 -0.1592 0.0091 1.0000 30.000 0.8880 0.40418 0.40238 -0.1624 0.0086 1.0000 30.500 0.8929 0.41278 0.41102 -0.1655 0.0083 1.0000 31.000 0.8989 0.42315 0.42142 -0.1678 0.0080 1.0000 31.500 0.9011 0.43339 0.43168 -0.1717 0.0079 1.0000 32.000 0.9044 0.44353 0.44184 -0.1752 0.0076 1.0000 32.500 0.9083 0.45349 0.45183 -0.1784 0.0068 1.0000 33.000 0.9114 0.46300 0.46137 -0.1815 0.0063 1.0000 33.500 0.9142 0.47245 0.47084 -0.1846 0.0058 1.0000 34.000 0.9165 0.48132 0.47976 -0.1876 0.0053 1.0000 34.500 0.9185 0.49027 0.48874 -0.1905 0.0052 1.0000