XFOIL Version 6.96 Calculated polar for: GOE 370 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.2012 0.09099 0.08892 -0.0397 0.9901 0.0079 -8.750 -0.1919 0.08719 0.08512 -0.0420 0.9844 0.0079 -6.750 -0.1774 0.07434 0.07213 -0.0616 0.9430 0.0048 -6.500 -0.1436 0.06929 0.06703 -0.0708 0.9286 0.0048 -6.250 -0.1115 0.06393 0.06158 -0.0797 0.9077 0.0051 -5.750 -0.0667 0.05795 0.05537 -0.0880 0.8662 0.0058 -5.500 -0.0457 0.05511 0.05243 -0.0913 0.8496 0.0069 -5.250 -0.0239 0.05134 0.04855 -0.0952 0.8350 0.0066 -5.000 0.0003 0.04742 0.04451 -0.0992 0.8229 0.0064 -4.750 0.0272 0.04319 0.04015 -0.1035 0.8131 0.0063 -4.000 0.1237 0.01312 0.00797 -0.1202 0.7918 0.0069 -3.750 0.1496 0.01175 0.00617 -0.1199 0.7856 0.0078 -3.500 0.1757 0.01065 0.00473 -0.1196 0.7793 0.0098 -3.250 0.2025 0.01023 0.00418 -0.1193 0.7738 0.0119 -3.000 0.2294 0.00984 0.00368 -0.1190 0.7683 0.0149 -2.750 0.2568 0.01005 0.00386 -0.1188 0.7629 0.0211 -2.500 0.2841 0.01012 0.00383 -0.1187 0.7578 0.0248 -2.250 0.3108 0.00992 0.00352 -0.1185 0.7521 0.0274 -1.750 0.3642 0.00951 0.00295 -0.1181 0.7414 0.0320 -1.500 0.3909 0.00928 0.00264 -0.1178 0.7361 0.0332 -1.250 0.4175 0.00903 0.00230 -0.1175 0.7313 0.0332 -1.000 0.4443 0.00880 0.00200 -0.1172 0.7259 0.0331 -0.750 0.4709 0.00864 0.00176 -0.1169 0.7205 0.0331 -0.500 0.4976 0.00850 0.00158 -0.1166 0.7148 0.0332 -0.250 0.5243 0.00840 0.00142 -0.1164 0.7086 0.0336 0.000 0.5509 0.00834 0.00130 -0.1161 0.7032 0.0343 0.250 0.5777 0.00827 0.00121 -0.1158 0.6967 0.0356 0.500 0.6040 0.00820 0.00114 -0.1155 0.6889 0.0444 0.750 0.6298 0.00810 0.00114 -0.1151 0.6777 0.0848 1.000 0.6557 0.00808 0.00117 -0.1147 0.6642 0.1087 1.250 0.6814 0.00811 0.00119 -0.1142 0.6488 0.1256 1.500 0.7070 0.00815 0.00123 -0.1138 0.6319 0.1395 1.750 0.7327 0.00821 0.00126 -0.1134 0.6150 0.1471 2.000 0.7583 0.00827 0.00131 -0.1129 0.5998 0.1569 2.250 0.7837 0.00833 0.00138 -0.1125 0.5847 0.1743 2.500 0.8089 0.00836 0.00151 -0.1120 0.5712 0.2152 2.750 0.8335 0.00827 0.00169 -0.1116 0.5599 0.3593 3.000 0.8738 0.00729 0.00190 -0.1148 0.5477 1.0000 3.250 0.8988 0.00745 0.00205 -0.1142 0.5367 1.0000 3.500 0.9240 0.00760 0.00221 -0.1137 0.5268 1.0000 3.750 0.9465 0.00792 0.00240 -0.1127 0.4968 1.0000 4.000 0.9684 0.00828 0.00262 -0.1116 0.4554 1.0000 4.250 0.9849 0.00910 0.00298 -0.1096 0.3549 1.0000 4.500 0.9983 0.01033 0.00361 -0.1073 0.2430 1.0000 4.750 1.0017 0.01264 0.00481 -0.1036 0.0287 1.0000 5.000 1.0236 0.01311 0.00528 -0.1025 0.0149 1.0000 5.250 1.0448 0.01369 0.00593 -0.1012 0.0096 1.0000 5.500 1.0665 0.01418 0.00653 -0.1001 0.0085 1.0000 5.750 1.0877 0.01471 0.00712 -0.0990 0.0071 1.0000 6.000 1.1068 0.01541 0.00788 -0.0975 0.0059 1.0000 6.250 1.1250 0.01621 0.00878 -0.0958 0.0054 1.0000 6.500 1.1422 0.01706 0.00973 -0.0940 0.0049 1.0000 6.750 1.1579 0.01803 0.01080 -0.0919 0.0045 1.0000 7.000 1.1724 0.01909 0.01197 -0.0896 0.0042 1.0000 7.250 1.1865 0.02021 0.01322 -0.0874 0.0040 1.0000 7.500 1.2015 0.02123 0.01429 -0.0854 0.0038 1.0000 7.750 1.2143 0.02261 0.01576 -0.0831 0.0033 1.0000 8.000 1.2304 0.02384 0.01715 -0.0812 0.0030 1.0000 8.250 1.2468 0.02577 0.01926 -0.0793 0.0027 1.0000 8.500 1.2660 0.02814 0.02185 -0.0779 0.0026 1.0000 8.750 1.2854 0.03080 0.02476 -0.0766 0.0024 1.0000 9.000 1.3026 0.03401 0.02828 -0.0749 0.0023 1.0000 9.250 1.3156 0.03784 0.03246 -0.0726 0.0023 1.0000 9.500 1.3228 0.04235 0.03737 -0.0695 0.0023 1.0000 9.750 1.3235 0.04681 0.04219 -0.0659 0.0024 1.0000 10.000 1.3196 0.05075 0.04644 -0.0620 0.0025 1.0000 10.250 1.3089 0.05413 0.05008 -0.0574 0.0026 1.0000 10.500 1.2953 0.05725 0.05341 -0.0531 0.0026 1.0000 10.750 1.2791 0.06068 0.05705 -0.0495 0.0027 1.0000 11.000 1.2627 0.06426 0.06083 -0.0468 0.0027 1.0000 11.250 1.2465 0.06803 0.06476 -0.0451 0.0028 1.0000 11.500 1.2282 0.07240 0.06931 -0.0443 0.0028 1.0000 11.750 1.2097 0.07716 0.07423 -0.0444 0.0028 1.0000 12.000 1.1903 0.08246 0.07969 -0.0453 0.0028 1.0000 12.250 1.1716 0.08818 0.08554 -0.0473 0.0029 1.0000