XFOIL Version 6.96 Calculated polar for: WORTMANN FX 62-K-131 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -14.250 -0.1606 0.13427 0.13265 -0.0721 0.9763 0.0051 -14.000 -0.1530 0.13115 0.12952 -0.0746 0.9702 0.0053 -13.750 -0.1435 0.12763 0.12599 -0.0776 0.9640 0.0054 -13.500 -0.1337 0.12397 0.12231 -0.0807 0.9578 0.0056 -13.250 -0.1236 0.12008 0.11838 -0.0840 0.9496 0.0059 -13.000 -0.1144 0.11615 0.11441 -0.0870 0.9371 0.0061 -12.750 -0.1089 0.11255 0.11072 -0.0890 0.9209 0.0063 -12.500 -0.1058 0.10919 0.10727 -0.0904 0.9069 0.0064 -12.250 -0.1025 0.10587 0.10390 -0.0914 0.8973 0.0065 -12.000 -0.0993 0.10259 0.10058 -0.0924 0.8898 0.0065 -11.750 -0.0964 0.09912 0.09708 -0.0933 0.8834 0.0065 -11.500 -0.0938 0.09562 0.09354 -0.0943 0.8782 0.0065 -11.250 -0.0916 0.09199 0.08990 -0.0952 0.8736 0.0065 -11.000 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0.00281 -0.1820 0.6579 0.7637 3.500 1.1402 0.00708 0.00293 -0.1815 0.6304 0.7659 3.750 1.1650 0.00731 0.00309 -0.1810 0.6052 0.7683 4.000 1.1883 0.00766 0.00331 -0.1803 0.5742 0.7709 4.250 1.2117 0.00802 0.00356 -0.1797 0.5443 0.7733 4.500 1.2323 0.00852 0.00388 -0.1785 0.5019 0.7753 4.750 1.2500 0.00919 0.00429 -0.1768 0.4435 0.7773 5.000 1.2644 0.01009 0.00483 -0.1745 0.3724 0.7795 5.250 1.2766 0.01114 0.00548 -0.1719 0.2968 0.7819 5.500 1.2878 0.01223 0.00617 -0.1692 0.2233 0.7843 5.750 1.2972 0.01341 0.00696 -0.1662 0.1515 0.7866 6.000 1.3099 0.01431 0.00762 -0.1638 0.1062 0.7888 6.250 1.3187 0.01527 0.00834 -0.1606 0.0636 0.7908 6.500 1.3279 0.01606 0.00900 -0.1574 0.0366 0.7928 6.750 1.3357 0.01710 0.00989 -0.1540 0.0107 0.7950 7.000 1.3486 0.01790 0.01065 -0.1516 0.0044 0.7973 7.250 1.3641 0.01856 0.01135 -0.1497 0.0035 0.7996 7.500 1.3790 0.01927 0.01213 -0.1478 0.0031 0.8015 7.750 1.3930 0.02001 0.01297 -0.1458 0.0029 0.8033 8.000 1.4068 0.02076 0.01380 -0.1438 0.0028 0.8051 8.250 1.4197 0.02160 0.01472 -0.1417 0.0027 0.8071 8.500 1.4322 0.02249 0.01569 -0.1397 0.0026 0.8091 8.750 1.4436 0.02350 0.01678 -0.1376 0.0025 0.8112 9.000 1.4543 0.02459 0.01795 -0.1355 0.0024 0.8132 9.250 1.4644 0.02578 0.01922 -0.1334 0.0023 0.8150 9.500 1.4733 0.02703 0.02056 -0.1312 0.0021 0.8169 9.750 1.4810 0.02843 0.02206 -0.1290 0.0020 0.8187 10.000 1.4850 0.03013 0.02386 -0.1264 0.0018 0.8205 10.250 1.4846 0.03227 0.02613 -0.1234 0.0017 0.8222 10.500 1.4795 0.03490 0.02891 -0.1200 0.0016 0.8241 10.750 1.4752 0.03754 0.03172 -0.1168 0.0016 0.8258 11.000 1.4713 0.04027 0.03459 -0.1138 0.0016 0.8274 11.250 1.4727 0.04254 0.03698 -0.1114 0.0016 0.8288 11.500 1.4736 0.04490 0.03947 -0.1091 0.0016 0.8304 11.750 1.4730 0.04754 0.04227 -0.1066 0.0016 0.8319 12.000 1.4750 0.04990 0.04476 -0.1046 0.0016 0.8334 12.250 1.4771 0.05226 0.04725 -0.1028 0.0016 0.8349 12.500 1.4781 0.05483 0.04996 -0.1011 0.0016 0.8365 12.750 1.4790 0.05746 0.05273 -0.0996 0.0016 0.8381 13.000 1.4790 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