XFOIL Version 6.96 Calculated polar for: FX 62-K-153/20 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.1677 0.10529 0.10255 -0.1086 0.9056 0.0161 -11.750 -0.1719 0.09959 0.09684 -0.1107 0.8998 0.0163 -11.500 -0.1679 0.09645 0.09366 -0.1117 0.8944 0.0166 -11.250 -0.1628 0.09334 0.09050 -0.1130 0.8899 0.0168 -11.000 -0.1583 0.09006 0.08722 -0.1146 0.8855 0.0171 -10.750 -0.1548 0.08646 0.08362 -0.1164 0.8811 0.0173 -10.500 -0.1524 0.08249 0.07962 -0.1187 0.8771 0.0176 -10.250 -0.1516 0.07796 0.07508 -0.1215 0.8735 0.0179 -10.000 -0.1533 0.07249 0.06963 -0.1254 0.8698 0.0181 -9.750 -0.1648 0.06295 0.06007 -0.1342 0.8657 0.0179 -9.500 -0.1831 0.05532 0.05229 -0.1411 0.8615 0.0178 -9.250 -0.2573 0.03847 0.03475 -0.1489 0.8541 0.0125 -9.000 -0.2482 0.03565 0.03177 -0.1501 0.8509 0.0111 -8.750 -0.2655 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-0.1745 0.7616 0.7130 1.000 0.8413 0.01070 0.00567 -0.1753 0.7592 0.7158 1.250 0.8725 0.01074 0.00568 -0.1763 0.7567 0.7188 1.500 0.8991 0.01074 0.00574 -0.1764 0.7531 0.7207 1.750 0.9266 0.01075 0.00580 -0.1765 0.7497 0.7223 2.000 0.9554 0.01075 0.00582 -0.1768 0.7467 0.7243 2.250 0.9856 0.01073 0.00578 -0.1775 0.7436 0.7264 2.500 1.0118 0.01069 0.00582 -0.1773 0.7381 0.7288 2.750 1.0407 0.01057 0.00570 -0.1776 0.7321 0.7312 3.000 1.0713 0.01052 0.00562 -0.1784 0.7275 0.7338 3.250 1.0969 0.01049 0.00568 -0.1781 0.7218 0.7357 3.500 1.1246 0.01042 0.00564 -0.1782 0.7163 0.7373 3.750 1.1508 0.01039 0.00567 -0.1780 0.7098 0.7391 4.000 1.1772 0.01033 0.00565 -0.1778 0.7019 0.7412 4.250 1.2027 0.01031 0.00568 -0.1775 0.6925 0.7436 4.500 1.2284 0.01028 0.00567 -0.1772 0.6810 0.7461 4.750 1.2534 0.01029 0.00567 -0.1767 0.6659 0.7483 5.000 1.2775 0.01034 0.00574 -0.1761 0.6515 0.7502 5.250 1.3007 0.01044 0.00587 -0.1753 0.6368 0.7520 5.500 1.3231 0.01060 0.00603 -0.1744 0.6201 0.7540 5.750 1.3430 0.01086 0.00623 -0.1730 0.5985 0.7560 6.000 1.3587 0.01126 0.00652 -0.1707 0.5657 0.7582 6.250 1.3708 0.01181 0.00692 -0.1679 0.5291 0.7605 6.500 1.3790 0.01246 0.00740 -0.1643 0.4923 0.7630 6.750 1.3813 0.01321 0.00798 -0.1597 0.4536 0.7651 7.000 1.3835 0.01418 0.00877 -0.1553 0.4110 0.7670 7.250 1.3827 0.01540 0.00975 -0.1507 0.3640 0.7690 7.500 1.3812 0.01679 0.01090 -0.1463 0.3137 0.7712 7.750 1.3802 0.01831 0.01218 -0.1423 0.2693 0.7734 8.000 1.3820 0.01982 0.01347 -0.1390 0.2302 0.7758 8.250 1.3869 0.02124 0.01472 -0.1363 0.1956 0.7781 8.750 1.3947 0.02425 0.01743 -0.1308 0.1326 0.7817 9.000 1.4010 0.02567 0.01874 -0.1285 0.1098 0.7836 9.250 1.4073 0.02713 0.02010 -0.1263 0.0913 0.7856 9.500 1.4163 0.02843 0.02138 -0.1244 0.0775 0.7879 9.750 1.4255 0.02975 0.02266 -0.1227 0.0663 0.7902 10.000 1.4361 0.03100 0.02390 -0.1212 0.0578 0.7924 10.250 1.4459 0.03226 0.02519 -0.1196 0.0504 0.7943 10.500 1.4539 0.03368 0.02660 -0.1178 0.0430 0.7962 10.750 1.4641 0.03495 0.02791 -0.1163 0.0376 0.7982 11.000 1.4727 0.03638 0.02936 -0.1147 0.0326 0.8004 11.250 1.4822 0.03776 0.03078 -0.1133 0.0288 0.8028 11.500 1.4902 0.03930 0.03235 -0.1118 0.0247 0.8052 11.750 1.4967 0.04101 0.03405 -0.1102 0.0196 0.8074 12.000 1.5020 0.04282 0.03589 -0.1086 0.0142 0.8095 12.250 1.5052 0.04486 0.03796 -0.1068 0.0100 0.8115 12.500 1.5096 0.04683 0.03998 -0.1052 0.0077 0.8137 12.750 1.5133 0.04895 0.04217 -0.1036 0.0066 0.8160 13.000 1.5191 0.05092 0.04424 -0.1024 0.0061 0.8184 13.250 1.5238 0.05304 0.04645 -0.1011 0.0056 0.8210 13.500 1.5271 0.05532 0.04883 -0.0999 0.0053 0.8234 13.750 1.5268 0.05799 0.05162 -0.0984 0.0049 0.8259 14.000 1.5270 0.06071 0.05447 -0.0972 0.0048 0.8285 14.250 1.5286 0.06335 0.05725 -0.0962 0.0046 0.8313 14.500 1.5289 0.06622 0.06024 -0.0953 0.0045 0.8341 14.750 1.5284 0.06923 0.06338 -0.0945 0.0044 0.8368 15.000 1.5269 0.07237 0.06666 -0.0938 0.0042 0.8395 15.250 1.5246 0.07570 0.07013 -0.0932 0.0041 0.8424 15.500 1.5218 0.07918 0.07374 -0.0927 0.0040 0.8457 15.750 1.5180 0.08289 0.07758 -0.0925 0.0039 0.8492 16.000 1.5129 0.08683 0.08166 -0.0924 0.0038 0.8526 16.250 1.5072 0.09087 0.08584 -0.0925 0.0038 0.8565 16.500 1.5002 0.09523 0.09034 -0.0927 0.0037 0.8608 16.750 1.4938 0.09959 0.09484 -0.0933 0.0037 0.8655 17.000 1.4860 0.10421 0.09961 -0.0940 0.0036 0.8707 17.250 1.4771 0.10908 0.10463 -0.0949 0.0036 0.8768 17.500 1.4692 0.11380 0.10950 -0.0960 0.0036 0.8846 18.000 1.4478 0.12319 0.11924 -0.0975 0.0035 0.9363 18.250 1.4382 0.12800 0.12419 -0.0990 0.0035 0.9999