XFOIL Version 6.96 Calculated polar for: FX 75-VG-166/22 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 ------ -------- --------- --------- -------- -------- -------- -15.500 -0.6227 0.07247 0.06830 -0.0964 0.7387 0.0084 -15.250 -0.6583 0.06204 0.05761 -0.1034 0.7384 0.0083 -15.000 -0.6897 0.05414 0.04946 -0.1077 0.7380 0.0084 -14.750 -0.6974 0.05026 0.04542 -0.1094 0.7376 0.0085 -14.500 -0.7087 0.04636 0.04134 -0.1102 0.7371 0.0085 -14.250 -0.7189 0.04294 0.03771 -0.1102 0.7366 0.0087 -14.000 -0.7212 0.04047 0.03507 -0.1099 0.7361 0.0089 -13.750 -0.7237 0.03805 0.03249 -0.1091 0.7356 0.0087 -13.500 -0.7233 0.03596 0.03021 -0.1081 0.7349 0.0090 -13.250 -0.7210 0.03405 0.02811 -0.1069 0.7343 0.0092 -13.000 -0.7154 0.03245 0.02637 -0.1058 0.7337 0.0092 -12.750 -0.7080 0.03099 0.02475 -0.1046 0.7331 0.0094 -12.500 -0.6979 0.02978 0.02339 -0.1034 0.7325 0.0096 -12.250 -0.6875 0.02858 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0.8131 7.000 0.8912 0.01364 0.00788 -0.0287 0.3747 0.8146 7.500 0.8771 0.01617 0.01020 -0.0196 0.3236 0.8175 7.750 0.8689 0.01757 0.01143 -0.0152 0.2897 0.8185 8.000 0.8661 0.01879 0.01248 -0.0116 0.2588 0.8193 8.250 0.8616 0.02013 0.01361 -0.0079 0.2219 0.8199 8.500 0.8665 0.02108 0.01444 -0.0055 0.1994 0.8204 8.750 0.8702 0.02213 0.01536 -0.0030 0.1715 0.8209 9.000 0.8790 0.02300 0.01615 -0.0012 0.1549 0.8213 9.250 0.8888 0.02385 0.01693 0.0004 0.1375 0.8217 9.500 0.8997 0.02467 0.01771 0.0018 0.1240 0.8221 10.000 0.9209 0.02646 0.01938 0.0046 0.0957 0.8227 10.250 0.9310 0.02743 0.02026 0.0059 0.0784 0.8230 10.500 0.9390 0.02855 0.02128 0.0073 0.0612 0.8233 10.750 0.9516 0.02946 0.02217 0.0082 0.0528 0.8236 11.000 0.9607 0.03065 0.02327 0.0093 0.0406 0.8238 11.250 0.9740 0.03159 0.02423 0.0101 0.0351 0.8240 11.500 0.9863 0.03265 0.02528 0.0108 0.0302 0.8242 11.750 0.9987 0.03373 0.02636 0.0115 0.0265 0.8244 12.000 1.0123 0.03475 0.02741 0.0120 0.0243 0.8246 12.250 1.0246 0.03590 0.02857 0.0126 0.0227 0.8248 12.500 1.0374 0.03702 0.02975 0.0131 0.0211 0.8249 12.750 1.0499 0.03820 0.03097 0.0136 0.0194 0.8251 13.000 1.0623 0.03941 0.03223 0.0140 0.0189 0.8254 13.250 1.0724 0.04084 0.03369 0.0145 0.0177 0.8255 13.500 1.0846 0.04213 0.03504 0.0148 0.0170 0.8256 13.750 1.0963 0.04348 0.03645 0.0151 0.0158 0.8257 14.000 1.1071 0.04492 0.03795 0.0154 0.0150 0.8260 14.250 1.1167 0.04651 0.03960 0.0157 0.0147 0.8263 14.500 1.1231 0.04842 0.04156 0.0160 0.0141 0.8267 14.750 1.1337 0.04996 0.04318 0.0162 0.0135 0.8273 15.000 1.1416 0.05179 0.04510 0.0164 0.0132 0.8275 15.250 1.1503 0.05359 0.04697 0.0165 0.0127 0.8278 15.500 1.1582 0.05551 0.04897 0.0164 0.0124 0.8280 15.750 1.1658 0.05751 0.05104 0.0163 0.0121 0.8280 16.000 1.1711 0.05978 0.05337 0.0162 0.0116 0.8280 16.250 1.1771 0.06201 0.05566 0.0160 0.0113 0.8281 16.500 1.1771 0.06495 0.05868 0.0158 0.0110 0.8281 16.750 1.1799 0.06763 0.06147 0.0155 0.0109 0.8281 17.000 1.1872 0.06988 0.06381 0.0150 0.0106 0.8282 17.250 1.1859 0.07316 0.06719 0.0145 0.0104 0.8282 17.500 1.1903 0.07579 0.06991 0.0139 0.0103 0.8282 17.750 1.1915 0.07888 0.07312 0.0132 0.0101 0.8282 18.000 1.1924 0.08205 0.07639 0.0123 0.0098 0.8283 18.250 1.1916 0.08551 0.07995 0.0114 0.0098 0.8283 18.500 1.1917 0.08891 0.08345 0.0103 0.0095 0.8283 18.750 1.1917 0.09238 0.08701 0.0091 0.0095 0.8283 19.000 1.1889 0.09626 0.09099 0.0077 0.0093 0.8283 19.250 1.1861 0.10021 0.09504 0.0062 0.0092 0.8284