XFOIL Version 6.96 Calculated polar for: WORTMANN FX 66-17A-175 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.6103 0.06439 0.06064 -0.0942 0.6533 0.0025 -15.000 -0.6241 0.05888 0.05500 -0.0974 0.6459 0.0026 -14.750 -0.6310 0.05471 0.05072 -0.0996 0.6383 0.0026 -14.500 -0.6166 0.05350 0.04949 -0.1003 0.6284 0.0028 -14.250 -0.6431 0.04766 0.04344 -0.1030 0.6227 0.0027 -14.000 -0.6406 0.04531 0.04103 -0.1039 0.6165 0.0028 -13.750 -0.6605 0.04086 0.03638 -0.1053 0.6109 0.0027 -13.500 -0.6550 0.03903 0.03448 -0.1058 0.6019 0.0028 -13.250 -0.6517 0.03703 0.03240 -0.1063 0.5952 0.0029 -13.000 -0.6525 0.03469 0.02995 -0.1067 0.5897 0.0029 -12.750 -0.6507 0.03263 0.02778 -0.1070 0.5828 0.0030 -12.500 -0.6511 0.03040 0.02544 -0.1071 0.5777 0.0031 -12.250 -0.6448 0.02878 0.02373 -0.1072 0.5723 0.0031 -12.000 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0.5280 8.250 1.2442 0.01668 0.00923 -0.0758 0.0833 0.5299 8.500 1.2106 0.01909 0.01138 -0.0674 0.0240 0.5314 9.000 1.2044 0.02216 0.01449 -0.0613 0.0046 0.5369 9.250 1.2083 0.02368 0.01607 -0.0598 0.0038 0.5403 9.500 1.2121 0.02541 0.01787 -0.0586 0.0033 0.5440 9.750 1.2158 0.02733 0.01986 -0.0576 0.0030 0.5476 10.000 1.2194 0.02933 0.02196 -0.0568 0.0028 0.5519 10.250 1.2217 0.03151 0.02421 -0.0561 0.0027 0.5565 10.500 1.2239 0.03370 0.02647 -0.0554 0.0026 0.5616 10.750 1.2232 0.03619 0.02904 -0.0546 0.0023 0.5666 11.000 1.2238 0.03854 0.03147 -0.0539 0.0022 0.5739 11.250 1.2229 0.04108 0.03410 -0.0532 0.0021 0.5805 11.500 1.2204 0.04378 0.03689 -0.0526 0.0020 0.5885 11.750 1.2190 0.04642 0.03962 -0.0520 0.0020 0.5979 12.000 1.2194 0.04894 0.04222 -0.0516 0.0019 0.6104 12.250 1.2173 0.05180 0.04519 -0.0512 0.0019 0.6247 12.500 1.2188 0.05434 0.04785 -0.0510 0.0019 0.6471 12.750 1.2205 0.05687 0.05055 -0.0508 0.0018 0.6878 13.250 1.2412 0.06231 0.05676 -0.0546 0.0016 1.0000 13.500 1.2434 0.06502 0.05952 -0.0547 0.0015 1.0000 13.750 1.2445 0.06792 0.06249 -0.0547 0.0015 1.0000 14.000 1.2467 0.07069 0.06530 -0.0548 0.0015 1.0000 14.250 1.2475 0.07369 0.06837 -0.0550 0.0014 1.0000 14.500 1.2510 0.07637 0.07110 -0.0552 0.0015 1.0000 14.750 1.2522 0.07943 0.07421 -0.0555 0.0014 1.0000 15.000 1.2518 0.08266 0.07751 -0.0558 0.0015 1.0000 15.250 1.2549 0.08549 0.08039 -0.0562 0.0013 1.0000