XFOIL Version 6.96 Calculated polar for: WORTMANN FX 3 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 ------ -------- --------- --------- -------- -------- -------- -19.250 -0.5765 0.11820 0.11417 -0.1095 0.8049 0.0087 -19.000 -0.6167 0.10610 0.10187 -0.1155 0.8049 0.0086 -18.750 -0.6448 0.09680 0.09239 -0.1204 0.8050 0.0086 -18.500 -0.6668 0.08892 0.08436 -0.1248 0.8050 0.0086 -18.250 -0.6851 0.08208 0.07738 -0.1286 0.8050 0.0086 -18.000 -0.6999 0.07614 0.07130 -0.1317 0.8050 0.0087 -17.750 -0.7119 0.07090 0.06594 -0.1344 0.8051 0.0087 -17.500 -0.7205 0.06639 0.06131 -0.1366 0.8051 0.0088 -17.250 -0.7261 0.06249 0.05730 -0.1384 0.8051 0.0089 -17.000 -0.7291 0.05905 0.05376 -0.1398 0.8051 0.0091 -16.750 -0.7295 0.05606 0.05067 -0.1409 0.8050 0.0092 -16.500 -0.7283 0.05339 0.04790 -0.1418 0.8050 0.0093 -16.250 -0.7254 0.05097 0.04538 -0.1425 0.8049 0.0095 -16.000 -0.7212 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0.7211 0.6917 4.750 0.7695 0.02914 0.02461 -0.1121 0.7083 0.6919 5.250 0.8243 0.02889 0.02441 -0.1130 0.6901 0.6921 5.500 0.8705 0.02744 0.02294 -0.1160 0.6744 0.6922 5.750 0.9648 0.02266 0.01788 -0.1255 0.6344 0.6922 6.000 0.9927 0.02225 0.01725 -0.1256 0.6003 0.6923 6.250 1.0056 0.02282 0.01765 -0.1237 0.5677 0.6924 6.500 1.0096 0.02390 0.01850 -0.1204 0.5258 0.6924 6.750 1.0092 0.02527 0.01959 -0.1166 0.4753 0.6925 7.000 1.0096 0.02668 0.02071 -0.1131 0.4232 0.6926 7.250 1.0114 0.02807 0.02178 -0.1098 0.3682 0.6926 7.500 1.0181 0.02923 0.02267 -0.1073 0.3174 0.6927 7.750 1.0253 0.03039 0.02354 -0.1049 0.2631 0.6927 8.000 1.0326 0.03158 0.02441 -0.1026 0.2072 0.6927 8.250 1.0426 0.03264 0.02522 -0.1007 0.1617 0.6928 8.500 1.0562 0.03355 0.02597 -0.0994 0.1320 0.6928 8.750 1.0708 0.03441 0.02672 -0.0982 0.1091 0.6929 9.000 1.0859 0.03526 0.02749 -0.0971 0.0920 0.6931 9.250 1.1018 0.03607 0.02825 -0.0961 0.0792 0.6933 9.500 1.1186 0.03684 0.02900 -0.0953 0.0699 0.6933 9.750 1.1348 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0.05619 -0.0731 0.0093 0.6938 15.000 1.3804 0.06521 0.05817 -0.0722 0.0091 0.6938 15.250 1.3873 0.06717 0.06023 -0.0713 0.0089 0.6939 15.500 1.3931 0.06929 0.06244 -0.0704 0.0087 0.6939 15.750 1.3989 0.07144 0.06468 -0.0696 0.0085 0.6940 16.000 1.4041 0.07370 0.06703 -0.0689 0.0082 0.6940 16.250 1.4090 0.07601 0.06943 -0.0682 0.0080 0.6940 16.500 1.4127 0.07849 0.07201 -0.0677 0.0078 0.6941 16.750 1.4163 0.08101 0.07462 -0.0672 0.0076 0.6941 17.000 1.4185 0.08372 0.07742 -0.0668 0.0075 0.6942 17.250 1.4187 0.08672 0.08051 -0.0664 0.0073 0.6942 17.500 1.4171 0.08999 0.08387 -0.0662 0.0072 0.6942 17.750 1.4147 0.09342 0.08740 -0.0660 0.0070 0.6943 18.000 1.4145 0.09662 0.09072 -0.0661 0.0069 0.6943 18.250 1.4136 0.09996 0.09418 -0.0663 0.0069 0.6944 18.500 1.4120 0.10344 0.09778 -0.0667 0.0068 0.6944 18.750 1.4097 0.10706 0.10153 -0.0673 0.0067 0.6944 19.000 1.4069 0.11080 0.10539 -0.0680 0.0066 0.6945 19.250 1.4034 0.11471 0.10943 -0.0689 0.0065 0.6945