XFOIL Version 6.96 Calculated polar for: LOCKHEED C-141 BL0 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5161 0.10114 0.09568 -0.0358 1.0000 0.1726 -10.000 -0.7758 0.06915 0.06346 -0.0457 1.0000 0.0890 -9.750 -0.7933 0.06581 0.06004 -0.0418 1.0000 0.0879 -9.500 -0.8137 0.06231 0.05640 -0.0373 1.0000 0.0869 -9.250 -0.8329 0.05860 0.05245 -0.0328 1.0000 0.0859 -9.000 -0.8483 0.05488 0.04842 -0.0283 1.0000 0.0853 -8.750 -0.8575 0.05135 0.04456 -0.0242 1.0000 0.0853 -8.500 -0.8614 0.04801 0.04086 -0.0204 1.0000 0.0856 -8.250 -0.8610 0.04478 0.03723 -0.0169 1.0000 0.0861 -8.000 -0.8566 0.04184 0.03387 -0.0137 1.0000 0.0870 -7.750 -0.8496 0.03941 0.03093 -0.0107 1.0000 0.0891 -7.500 -0.8397 0.03709 0.02810 -0.0079 1.0000 0.0914 -7.250 -0.8226 0.03500 0.02600 -0.0067 1.0000 0.0942 -7.000 -0.8047 0.03365 0.02454 -0.0052 1.0000 0.0979 -6.750 -0.7875 0.03222 0.02272 -0.0034 1.0000 0.1021 -6.500 -0.7676 0.03043 0.02070 -0.0022 1.0000 0.1059 -6.250 -0.7471 0.02936 0.01962 -0.0012 1.0000 0.1110 -6.000 -0.7263 0.02834 0.01833 0.0002 1.0000 0.1166 -5.750 -0.7042 0.02699 0.01702 0.0009 1.0000 0.1224 -5.500 -0.6828 0.02618 0.01611 0.0020 1.0000 0.1298 -5.250 -0.6607 0.02511 0.01506 0.0029 1.0000 0.1373 -5.000 -0.6393 0.02444 0.01428 0.0040 1.0000 0.1471 -4.750 -0.6178 0.02350 0.01352 0.0049 1.0000 0.1580 -4.500 -0.5967 0.02271 0.01281 0.0059 1.0000 0.1719 -4.250 -0.5760 0.02195 0.01218 0.0070 1.0000 0.1901 -4.000 -0.5558 0.02116 0.01157 0.0081 1.0000 0.2158 -3.750 -0.5363 0.02023 0.01101 0.0093 1.0000 0.2589 -3.500 -0.5194 0.01870 0.01049 0.0106 1.0000 0.3875 -3.250 -0.5067 0.01772 0.01089 0.0144 1.0000 0.6386 -3.000 -0.4908 0.01785 0.01124 0.0178 1.0000 0.7301 -2.750 -0.4742 0.01808 0.01155 0.0210 1.0000 0.7845 -2.500 -0.4571 0.01842 0.01193 0.0242 1.0000 0.8273 -2.250 -0.4383 0.01886 0.01236 0.0271 1.0000 0.8648 -2.000 -0.4130 0.01944 0.01289 0.0286 1.0000 0.8988 -1.750 -0.3745 0.02025 0.01360 0.0273 1.0000 0.9289 -1.500 -0.3171 0.02128 0.01447 0.0220 1.0000 0.9536 -1.250 -0.2362 0.02245 0.01545 0.0117 1.0000 0.9721 -1.000 -0.1252 0.02367 0.01647 -0.0045 1.0000 0.9940 -0.750 -0.0912 0.02368 0.01642 -0.0076 1.0000 1.0000 -0.500 -0.0950 0.02337 0.01608 -0.0038 1.0000 1.0000 -0.250 -0.0995 0.02306 0.01574 0.0001 1.0000 1.0000 0.000 -0.1039 0.02279 0.01544 0.0041 1.0000 1.0000 0.250 -0.0616 0.02321 0.01580 -0.0003 0.9921 1.0000 0.500 -0.0209 0.02366 0.01620 -0.0043 0.9837 1.0000 0.750 0.0146 0.02396 0.01648 -0.0071 0.9737 1.0000 1.000 0.0479 0.02426 0.01676 -0.0094 0.9635 1.0000 1.250 0.0842 0.02464 0.01712 -0.0121 0.9540 1.0000 1.500 0.1212 0.02497 0.01746 -0.0147 0.9442 1.0000 1.750 0.1509 0.02520 0.01769 -0.0159 0.9323 1.0000 2.000 0.1871 0.02547 0.01798 -0.0182 0.9213 1.0000 2.250 0.2397 0.02567 0.01823 -0.0231 0.9116 1.0000 2.500 0.2861 0.02549 0.01812 -0.0264 0.8965 1.0000 2.750 0.3439 0.02496 0.01768 -0.0312 0.8807 1.0000 3.000 0.3970 0.02427 0.01711 -0.0350 0.8652 1.0000 3.250 0.4467 0.02349 0.01645 -0.0380 0.8502 1.0000 3.500 0.4993 0.02247 0.01559 -0.0412 0.8353 1.0000 3.750 0.5574 0.02106 0.01436 -0.0449 0.8200 1.0000 4.000 0.6081 0.01953 0.01300 -0.0470 0.8015 1.0000 4.250 0.6383 0.01843 0.01201 -0.0456 0.7760 1.0000 4.500 0.6701 0.01734 0.01102 -0.0444 0.7391 1.0000 4.750 0.7219 0.01617 0.00966 -0.0462 0.6514 1.0000 5.000 0.7387 0.01672 0.00919 -0.0425 0.4646 1.0000 5.250 0.7309 0.01818 0.00964 -0.0358 0.3300 1.0000 5.500 0.7311 0.01948 0.01033 -0.0308 0.2629 1.0000 5.750 0.7381 0.02055 0.01105 -0.0271 0.2242 1.0000 6.000 0.7497 0.02159 0.01181 -0.0242 0.1983 1.0000 6.250 0.7649 0.02253 0.01261 -0.0220 0.1778 1.0000 6.500 0.7834 0.02354 0.01350 -0.0203 0.1617 1.0000 6.750 0.8044 0.02462 0.01448 -0.0192 0.1484 1.0000 7.000 0.8287 0.02586 0.01557 -0.0187 0.1372 1.0000 7.250 0.8501 0.02684 0.01659 -0.0176 0.1278 1.0000 7.500 0.8760 0.02826 0.01804 -0.0173 0.1197 1.0000 7.750 0.8986 0.02942 0.01918 -0.0165 0.1126 1.0000 8.000 0.9237 0.03113 0.02101 -0.0161 0.1068 1.0000 8.250 0.9434 0.03237 0.02239 -0.0146 0.1013 1.0000 8.500 0.9706 0.03465 0.02458 -0.0151 0.0966 1.0000 8.750 0.9826 0.03604 0.02640 -0.0121 0.0932 1.0000 9.000 0.9981 0.03763 0.02822 -0.0100 0.0895 1.0000 9.250 1.0171 0.03944 0.03010 -0.0089 0.0866 1.0000 9.500 1.0334 0.04244 0.03322 -0.0077 0.0842 1.0000 9.750 1.0353 0.04447 0.03576 -0.0035 0.0825 1.0000 10.000 1.0364 0.04696 0.03867 0.0004 0.0808 1.0000 10.250 1.0356 0.04984 0.04193 0.0042 0.0799 1.0000 10.500 1.0305 0.05307 0.04553 0.0082 0.0796 1.0000 10.750 1.0206 0.05655 0.04935 0.0124 0.0797 1.0000 11.000 1.0055 0.06008 0.05318 0.0168 0.0800 1.0000 11.250 0.9847 0.06353 0.05689 0.0216 0.0805 1.0000 11.500 0.9604 0.06730 0.06089 0.0256 0.0811 1.0000 11.750 0.9355 0.07147 0.06525 0.0286 0.0818 1.0000 12.000 0.9117 0.07607 0.07001 0.0302 0.0826 1.0000 12.250 0.8913 0.08109 0.07515 0.0308 0.0833 1.0000 12.500 0.8788 0.08635 0.08048 0.0306 0.0839 1.0000