XFOIL Version 6.96 Calculated polar for: FX LIII-142 K 25 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.8461 0.12085 0.11556 0.0033 1.0000 0.0489 -15.500 -0.9085 0.10277 0.09735 -0.0080 1.0000 0.0479 -15.250 -0.9486 0.09134 0.08571 -0.0151 1.0000 0.0473 -15.000 -0.9799 0.08270 0.07682 -0.0202 1.0000 0.0473 -14.750 -1.0038 0.07588 0.06975 -0.0238 1.0000 0.0476 -14.500 -1.0243 0.07007 0.06368 -0.0267 1.0000 0.0483 -14.250 -1.0419 0.06502 0.05835 -0.0289 1.0000 0.0490 -14.000 -1.0442 0.06188 0.05517 -0.0296 1.0000 0.0505 -13.750 -1.0418 0.05959 0.05289 -0.0302 1.0000 0.0522 -13.500 -1.0441 0.05675 0.04994 -0.0308 1.0000 0.0536 -13.250 -1.0471 0.05381 0.04684 -0.0312 1.0000 0.0549 -13.000 -1.0488 0.05099 0.04381 -0.0313 1.0000 0.0562 -12.750 -1.0490 0.04835 0.04092 -0.0311 1.0000 0.0575 -12.500 -1.0486 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0.7511 0.5623 -3.000 -0.3246 0.01660 0.00787 -0.0029 0.7425 0.5727 -2.750 -0.2978 0.01660 0.00782 -0.0025 0.7334 0.5809 -2.500 -0.2710 0.01661 0.00768 -0.0022 0.7256 0.5904 -2.250 -0.2438 0.01662 0.00769 -0.0019 0.7167 0.5975 -2.000 -0.2171 0.01659 0.00753 -0.0016 0.7095 0.6060 -1.750 -0.1898 0.01655 0.00750 -0.0014 0.7014 0.6118 -1.500 -0.1629 0.01652 0.00735 -0.0012 0.6951 0.6192 -1.250 -0.1357 0.01646 0.00732 -0.0011 0.6873 0.6249 -1.000 -0.1086 0.01643 0.00723 -0.0008 0.6811 0.6316 -0.750 -0.0815 0.01639 0.00719 -0.0007 0.6743 0.6379 -0.500 -0.0543 0.01637 0.00718 -0.0004 0.6680 0.6440 -0.250 -0.0272 0.01636 0.00713 -0.0002 0.6625 0.6506 0.000 0.0000 0.01636 0.00717 0.0000 0.6559 0.6560 0.250 0.0272 0.01636 0.00713 0.0002 0.6506 0.6625 0.500 0.0543 0.01637 0.00718 0.0004 0.6440 0.6680 0.750 0.0815 0.01639 0.00719 0.0007 0.6379 0.6742 1.000 0.1086 0.01643 0.00723 0.0008 0.6316 0.6811 1.250 0.1357 0.01646 0.00732 0.0011 0.6249 0.6873 1.500 0.1629 0.01652 0.00735 0.0012 0.6193 0.6951 1.750 0.1898 0.01655 0.00750 0.0014 0.6118 0.7014 2.000 0.2171 0.01659 0.00754 0.0017 0.6060 0.7095 2.250 0.2438 0.01662 0.00769 0.0019 0.5975 0.7168 2.500 0.2710 0.01661 0.00768 0.0022 0.5903 0.7257 2.750 0.2978 0.01660 0.00782 0.0025 0.5810 0.7334 3.000 0.3246 0.01659 0.00787 0.0029 0.5726 0.7425 3.250 0.3513 0.01654 0.00789 0.0035 0.5623 0.7512 3.500 0.3773 0.01648 0.00797 0.0041 0.5487 0.7603 3.750 0.4031 0.01639 0.00800 0.0048 0.5344 0.7707 4.000 0.4290 0.01632 0.00803 0.0055 0.5207 0.7836 4.250 0.4550 0.01632 0.00811 0.0060 0.5092 0.8002 4.500 0.4814 0.01632 0.00821 0.0065 0.4983 0.8163 4.750 0.5082 0.01631 0.00835 0.0070 0.4845 0.8327 5.000 0.5356 0.01628 0.00852 0.0072 0.4641 0.8518 5.250 0.5647 0.01618 0.00851 0.0072 0.4374 0.8751 5.500 0.5986 0.01622 0.00853 0.0062 0.4001 0.9011 5.750 0.6343 0.01648 0.00869 0.0045 0.3531 0.9357 6.000 0.6729 0.01698 0.00902 0.0017 0.3023 0.9747 6.250 0.6994 0.01771 0.00951 0.0011 0.2566 1.0000 6.500 0.7161 0.01844 0.01005 0.0024 0.2223 1.0000 6.750 0.7336 0.01920 0.01065 0.0037 0.1946 1.0000 7.000 0.7508 0.02000 0.01131 0.0049 0.1736 1.0000 7.250 0.7682 0.02080 0.01203 0.0061 0.1561 1.0000 7.500 0.7854 0.02162 0.01281 0.0073 0.1408 1.0000 7.750 0.8025 0.02245 0.01359 0.0085 0.1277 1.0000 8.000 0.8192 0.02329 0.01441 0.0097 0.1176 1.0000 8.250 0.8358 0.02414 0.01529 0.0110 0.1091 1.0000 8.500 0.8509 0.02508 0.01620 0.0124 0.1024 1.0000 8.750 0.8666 0.02602 0.01716 0.0138 0.0967 1.0000 9.000 0.8825 0.02692 0.01813 0.0151 0.0915 1.0000 9.250 0.8964 0.02791 0.01910 0.0165 0.0875 1.0000 9.500 0.9115 0.02889 0.02013 0.0178 0.0839 1.0000 9.750 0.9263 0.02988 0.02119 0.0191 0.0805 1.0000 10.000 0.9399 0.03092 0.02227 0.0205 0.0781 1.0000 10.250 0.9520 0.03204 0.02339 0.0220 0.0758 1.0000 10.500 0.9656 0.03334 0.02462 0.0233 0.0736 1.0000 10.750 0.9790 0.03454 0.02604 0.0245 0.0715 1.0000 11.000 0.9913 0.03585 0.02750 0.0257 0.0692 1.0000 11.250 1.0030 0.03723 0.02900 0.0267 0.0670 1.0000 11.500 1.0147 0.03871 0.03059 0.0277 0.0653 1.0000 11.750 1.0257 0.04026 0.03221 0.0286 0.0638 1.0000 12.000 1.0364 0.04188 0.03385 0.0293 0.0620 1.0000 12.250 1.0470 0.04386 0.03590 0.0300 0.0603 1.0000 12.500 1.0491 0.04597 0.03828 0.0306 0.0590 1.0000 12.750 1.0498 0.04835 0.04092 0.0310 0.0575 1.0000 13.000 1.0494 0.05101 0.04383 0.0312 0.0561 1.0000 13.250 1.0475 0.05380 0.04682 0.0310 0.0548 1.0000 13.500 1.0448 0.05671 0.04989 0.0306 0.0534 1.0000 13.750 1.0430 0.05951 0.05280 0.0301 0.0521 1.0000 14.000 1.0457 0.06180 0.05508 0.0296 0.0504 1.0000 14.250 1.0428 0.06504 0.05836 0.0288 0.0490 1.0000 14.500 1.0254 0.07007 0.06369 0.0266 0.0483 1.0000 14.750 1.0046 0.07594 0.06982 0.0237 0.0477 1.0000 15.000 0.9800 0.08281 0.07694 0.0199 0.0472 1.0000 15.250 0.9490 0.09148 0.08584 0.0148 0.0472 1.0000 15.500 0.9091 0.10290 0.09748 0.0078 0.0479 1.0000 15.750 0.8443 0.12165 0.11637 -0.0039 0.0489 1.0000