XFOIL Version 6.96 Calculated polar for: FX 74-130 WP1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.0841 0.08328 0.08076 -0.1097 0.8182 0.0097 -11.000 -0.0811 0.07981 0.07728 -0.1109 0.8170 0.0099 -10.750 -0.0789 0.07606 0.07354 -0.1123 0.8163 0.0099 -10.500 -0.0758 0.07277 0.07026 -0.1133 0.8155 0.0101 -10.250 -0.0743 0.06909 0.06658 -0.1146 0.8147 0.0102 -10.000 -0.0740 0.06514 0.06264 -0.1161 0.8138 0.0102 -9.750 -0.0738 0.06137 0.05889 -0.1175 0.8128 0.0103 -9.500 -0.0743 0.05755 0.05508 -0.1189 0.8118 0.0104 -9.250 -0.0772 0.05334 0.05089 -0.1207 0.8107 0.0106 -9.000 -0.0827 0.04874 0.04631 -0.1230 0.8094 0.0106 -8.750 -0.0995 0.04221 0.03979 -0.1286 0.8079 0.0104 -8.500 -0.1228 0.03683 0.03435 -0.1314 0.8062 0.0103 -8.250 -0.1442 0.03350 0.03097 -0.1303 0.8044 0.0103 -8.000 -0.1542 0.03048 0.02785 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0.8816 11.500 1.3242 0.02960 0.02347 -0.0620 0.0095 0.8828 11.750 1.3386 0.03050 0.02442 -0.0611 0.0086 0.8840 12.000 1.3524 0.03147 0.02544 -0.0601 0.0081 0.8853 12.250 1.3575 0.03322 0.02725 -0.0583 0.0070 0.8866 12.500 1.3684 0.03450 0.02862 -0.0571 0.0066 0.8879 12.750 1.3811 0.03565 0.02984 -0.0562 0.0063 0.8893 13.000 1.3918 0.03701 0.03128 -0.0551 0.0060 0.8906 13.250 1.4017 0.03843 0.03277 -0.0540 0.0057 0.8924 13.500 1.4124 0.03979 0.03421 -0.0531 0.0054 0.8943 13.750 1.4211 0.04137 0.03586 -0.0521 0.0051 0.8964 14.000 1.4262 0.04337 0.03796 -0.0509 0.0049 0.8986 14.250 1.4178 0.04689 0.04167 -0.0488 0.0045 0.9005 14.500 1.4282 0.04844 0.04331 -0.0482 0.0044 0.9033 14.750 1.4340 0.05053 0.04554 -0.0474 0.0043 0.9064 15.000 1.4403 0.05255 0.04767 -0.0466 0.0042 0.9109 15.250 1.4444 0.05485 0.05012 -0.0459 0.0041 0.9164 15.500 1.4457 0.05736 0.05278 -0.0449 0.0040 0.9267 15.750 1.4431 0.05984 0.05547 -0.0434 0.0039 1.0000 16.000 1.4448 0.06278 0.05852 -0.0432 0.0038 1.0000 16.250 1.4438 0.06615 0.06203 -0.0430 0.0037 1.0000 16.500 1.4427 0.06960 0.06561 -0.0430 0.0037 1.0000 16.750 1.4403 0.07331 0.06945 -0.0433 0.0036 1.0000 17.000 1.4362 0.07740 0.07369 -0.0437 0.0036 1.0000 17.250 1.4306 0.08185 0.07828 -0.0445 0.0035 1.0000 17.500 1.4245 0.08649 0.08307 -0.0455 0.0035 1.0000 17.750 1.4164 0.09161 0.08834 -0.0469 0.0035 1.0000 18.000 1.4072 0.09708 0.09396 -0.0487 0.0034 1.0000 18.250 1.3969 0.10293 0.09997 -0.0509 0.0034 1.0000 18.500 1.3850 0.10929 0.10648 -0.0535 0.0034 1.0000 18.750 1.3717 0.11609 0.11345 -0.0567 0.0034 1.0000 19.000 1.3568 0.12342 0.12095 -0.0605 0.0034 1.0000 19.250 1.3408 0.13126 0.12896 -0.0648 0.0034 1.0000