XFOIL Version 6.96 Calculated polar for: FX 63-158 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 ------ -------- --------- --------- -------- -------- -------- -11.000 -0.0600 0.07872 0.07515 -0.1064 0.6989 0.0133 -10.500 -0.1044 0.05342 0.05003 -0.1176 0.7385 0.0088 -10.250 -0.1171 0.04810 0.04461 -0.1208 0.7209 0.0087 -10.000 -0.1363 0.04171 0.03818 -0.1248 0.7298 0.0086 -9.750 -0.1552 0.03746 0.03370 -0.1263 0.6989 0.0086 -9.500 -0.1716 0.03385 0.02996 -0.1271 0.6887 0.0085 -9.250 -0.1850 0.03099 0.02697 -0.1270 0.6811 0.0084 -9.000 -0.2000 0.02835 0.02420 -0.1260 0.6740 0.0083 -8.750 -0.2149 0.02642 0.02210 -0.1237 0.6607 0.0082 -8.250 -0.2518 0.03032 0.02501 -0.1248 0.6606 0.0065 -8.000 -0.2433 0.02828 0.02269 -0.1236 0.6408 0.0064 -7.750 -0.2308 0.02624 0.02036 -0.1226 0.6269 0.0064 -7.500 -0.2163 0.02417 0.01794 -0.1214 0.6104 0.0063 -7.250 -0.1987 0.02240 0.01586 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2.500 0.8654 0.01379 0.00499 -0.1305 0.0964 0.6367 2.750 0.8912 0.01401 0.00523 -0.1302 0.0954 0.6441 3.000 0.9171 0.01425 0.00545 -0.1300 0.0943 0.6528 3.250 0.9424 0.01449 0.00570 -0.1297 0.0931 0.6590 3.500 0.9678 0.01472 0.00594 -0.1294 0.0919 0.6642 3.750 0.9932 0.01496 0.00617 -0.1291 0.0902 0.6673 4.000 1.0186 0.01520 0.00640 -0.1289 0.0884 0.6705 4.250 1.0435 0.01542 0.00665 -0.1285 0.0871 0.6731 4.500 1.0679 0.01566 0.00693 -0.1281 0.0857 0.6755 4.750 1.0922 0.01591 0.00720 -0.1276 0.0846 0.6777 5.000 1.1163 0.01617 0.00748 -0.1272 0.0836 0.6801 5.250 1.1400 0.01644 0.00778 -0.1266 0.0826 0.6825 5.500 1.1633 0.01673 0.00809 -0.1261 0.0816 0.6849 5.750 1.1862 0.01704 0.00842 -0.1254 0.0806 0.6871 6.000 1.2088 0.01732 0.00874 -0.1247 0.0798 0.6892 6.250 1.2313 0.01757 0.00905 -0.1240 0.0791 0.6913 6.500 1.2529 0.01783 0.00937 -0.1231 0.0782 0.6934 6.750 1.2735 0.01809 0.00968 -0.1220 0.0761 0.6956 7.000 1.2914 0.01847 0.01009 -0.1205 0.0639 0.6978 7.250 1.3065 0.01901 0.01059 -0.1186 0.0617 0.6999 7.500 1.3224 0.01953 0.01110 -0.1168 0.0590 0.7019 7.750 1.3391 0.02001 0.01163 -0.1153 0.0576 0.7037 8.000 1.3550 0.02053 0.01220 -0.1136 0.0568 0.7053 8.250 1.3689 0.02114 0.01289 -0.1117 0.0555 0.7067 8.500 1.3800 0.02191 0.01373 -0.1095 0.0539 0.7078 8.750 1.3888 0.02283 0.01472 -0.1071 0.0519 0.7089 9.000 1.4010 0.02359 0.01555 -0.1053 0.0505 0.7101 9.250 1.4156 0.02425 0.01629 -0.1039 0.0491 0.7115 9.500 1.4286 0.02502 0.01716 -0.1023 0.0471 0.7130 9.750 1.4400 0.02594 0.01815 -0.1007 0.0450 0.7147 10.000 1.4510 0.02693 0.01921 -0.0992 0.0434 0.7163 10.250 1.4642 0.02782 0.02018 -0.0981 0.0410 0.7176 10.500 1.4741 0.02900 0.02140 -0.0967 0.0347 0.7189 10.750 1.4787 0.03065 0.02302 -0.0951 0.0305 0.7201 11.000 1.4843 0.03234 0.02476 -0.0939 0.0281 0.7212 11.250 1.4882 0.03428 0.02675 -0.0927 0.0260 0.7223 11.500 1.4914 0.03638 0.02892 -0.0916 0.0241 0.7235 11.750 1.4975 0.03832 0.03095 -0.0909 0.0228 0.7247 12.000 1.5025 0.04043 0.03316 -0.0903 0.0205 0.7259 12.250 1.5045 0.04294 0.03573 -0.0897 0.0177 0.7271 12.500 1.5059 0.04558 0.03842 -0.0892 0.0155 0.7284 12.750 1.5060 0.04844 0.04133 -0.0889 0.0134 0.7297 13.000 1.5075 0.05122 0.04419 -0.0887 0.0120 0.7311 13.250 1.5078 0.05421 0.04724 -0.0885 0.0106 0.7326 13.500 1.5095 0.05711 0.05022 -0.0885 0.0095 0.7342 14.000 1.5035 0.06434 0.05756 -0.0889 0.0033 0.7369 14.250 1.5016 0.06796 0.06127 -0.0892 0.0029 0.7381 14.500 1.5010 0.07151 0.06491 -0.0897 0.0027 0.7393 14.750 1.5012 0.07499 0.06850 -0.0902 0.0025 0.7404 15.000 1.5016 0.07854 0.07216 -0.0909 0.0024 0.7417 15.250 1.5023 0.08213 0.07586 -0.0916 0.0023 0.7429 15.500 1.5025 0.08583 0.07969 -0.0925 0.0022 0.7443 15.750 1.5023 0.08965 0.08363 -0.0934 0.0022 0.7456 16.000 1.5022 0.09350 0.08758 -0.0945 0.0021 0.7471 16.250 1.5014 0.09752 0.09173 -0.0956 0.0021 0.7485 16.500 1.5005 0.10162 0.09594 -0.0969 0.0020 0.7500 16.750 1.4991 0.10583 0.10028 -0.0983 0.0020 0.7515 17.000 1.4977 0.11009 0.10465 -0.0998 0.0019 0.7530 17.250 1.4960 0.11442 0.10911 -0.1014 0.0019 0.7545 17.500 1.4936 0.11892 0.11372 -0.1031 0.0018 0.7559 17.750 1.4911 0.12345 0.11838 -0.1050 0.0018 0.7573 18.000 1.4884 0.12807 0.12313 -0.1070 0.0017 0.7589 18.250 1.4845 0.13294 0.12814 -0.1093 0.0017 0.7605 18.500 1.4799 0.13799 0.13331 -0.1118 0.0016 0.7621