XFOIL Version 6.96 Calculated polar for: LOCKHEED C-141 BL113.6 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -0.8548 0.12785 0.12476 -0.0321 1.0000 0.0144 -18.000 -0.9145 0.11156 0.10824 -0.0406 1.0000 0.0143 -17.750 -0.9578 0.09926 0.09577 -0.0472 1.0000 0.0142 -17.500 -0.9937 0.08861 0.08493 -0.0530 1.0000 0.0142 -17.250 -1.0238 0.07909 0.07524 -0.0585 1.0000 0.0141 -17.000 -1.0489 0.07072 0.06670 -0.0634 1.0000 0.0141 -16.750 -1.0692 0.06352 0.05933 -0.0677 1.0000 0.0142 -16.500 -1.0860 0.05738 0.05304 -0.0712 1.0000 0.0142 -16.250 -1.0994 0.05220 0.04772 -0.0739 1.0000 0.0143 -16.000 -1.1092 0.04789 0.04328 -0.0757 1.0000 0.0144 -15.750 -1.1159 0.04430 0.03957 -0.0768 1.0000 0.0145 -15.500 -1.1199 0.04127 0.03643 -0.0773 1.0000 0.0147 -15.250 -1.1218 0.03870 0.03375 -0.0773 1.0000 0.0148 -15.000 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0.00457 -0.0536 0.9278 0.0669 -5.250 -0.3616 0.01135 0.00438 -0.0530 0.9247 0.0726 -5.000 -0.3376 0.01113 0.00420 -0.0523 0.9211 0.0797 -4.750 -0.3120 0.01092 0.00400 -0.0519 0.9180 0.0883 -4.250 -0.2586 0.01045 0.00362 -0.0517 0.9131 0.1117 -4.000 -0.2319 0.01021 0.00344 -0.0515 0.9107 0.1277 -3.750 -0.2086 0.01000 0.00331 -0.0507 0.9067 0.1471 -3.500 -0.1837 0.00977 0.00317 -0.0502 0.9032 0.1714 -3.250 -0.1581 0.00949 0.00301 -0.0499 0.9000 0.2017 -3.000 -0.1323 0.00916 0.00284 -0.0496 0.8973 0.2429 -2.750 -0.1076 0.00881 0.00269 -0.0491 0.8942 0.2968 -2.500 -0.0864 0.00842 0.00257 -0.0479 0.8896 0.3663 -2.250 -0.0645 0.00797 0.00244 -0.0469 0.8855 0.4497 -2.000 -0.0406 0.00761 0.00233 -0.0461 0.8821 0.5210 -1.750 -0.0153 0.00735 0.00226 -0.0456 0.8788 0.5746 -1.500 0.0077 0.00720 0.00226 -0.0445 0.8739 0.6151 -1.250 0.0332 0.00708 0.00223 -0.0439 0.8694 0.6465 -1.000 0.0606 0.00697 0.00219 -0.0437 0.8656 0.6732 -0.750 0.0872 0.00689 0.00218 -0.0433 0.8614 0.6971 -0.500 0.1124 0.00683 0.00220 -0.0427 0.8557 0.7183 -0.250 0.1393 0.00676 0.00218 -0.0423 0.8506 0.7403 0.000 0.1660 0.00666 0.00218 -0.0419 0.8456 0.7654 0.250 0.1910 0.00660 0.00221 -0.0411 0.8379 0.7844 0.500 0.2176 0.00653 0.00215 -0.0406 0.8252 0.7961 0.750 0.2432 0.00647 0.00204 -0.0398 0.8013 0.8073 1.000 0.2687 0.00645 0.00197 -0.0390 0.7736 0.8179 1.250 0.2943 0.00648 0.00194 -0.0383 0.7470 0.8288 1.500 0.3184 0.00659 0.00194 -0.0373 0.7146 0.8406 1.750 0.3418 0.00674 0.00199 -0.0362 0.6823 0.8520 2.000 0.3645 0.00693 0.00208 -0.0349 0.6476 0.8636 2.250 0.3855 0.00719 0.00218 -0.0334 0.6052 0.8761 2.500 0.4059 0.00750 0.00233 -0.0317 0.5555 0.8884 2.750 0.4252 0.00791 0.00252 -0.0299 0.4940 0.9004 3.000 0.4430 0.00846 0.00276 -0.0279 0.4179 0.9129 3.250 0.4615 0.00905 0.00303 -0.0262 0.3419 0.9254 3.500 0.4841 0.00959 0.00331 -0.0253 0.2791 0.9355 3.750 0.5079 0.01005 0.00356 -0.0247 0.2311 0.9446 4.250 0.5606 0.01086 0.00406 -0.0245 0.1636 0.9601 4.500 0.5883 0.01121 0.00431 -0.0248 0.1405 0.9668 4.750 0.6165 0.01156 0.00456 -0.0251 0.1211 0.9724 5.000 0.6472 0.01191 0.00483 -0.0260 0.1052 0.9765 5.250 0.6760 0.01223 0.00509 -0.0265 0.0932 0.9815 5.500 0.7073 0.01256 0.00537 -0.0275 0.0827 0.9846 5.750 0.7395 0.01289 0.00566 -0.0288 0.0742 0.9872 6.000 0.7702 0.01324 0.00597 -0.0297 0.0667 0.9905 6.250 0.7996 0.01358 0.00627 -0.0304 0.0606 0.9938 6.500 0.8313 0.01392 0.00661 -0.0316 0.0554 0.9960 6.750 0.8622 0.01431 0.00695 -0.0327 0.0504 0.9985 7.000 0.8875 0.01462 0.00728 -0.0325 0.0470 1.0000 7.250 0.9014 0.01489 0.00754 -0.0298 0.0442 1.0000 7.500 0.9153 0.01518 0.00783 -0.0272 0.0419 1.0000 7.750 0.9301 0.01545 0.00812 -0.0247 0.0399 1.0000 8.000 0.9437 0.01574 0.00842 -0.0220 0.0379 1.0000 8.250 0.9559 0.01608 0.00874 -0.0191 0.0361 1.0000 8.500 0.9706 0.01637 0.00907 -0.0166 0.0346 1.0000 8.750 0.9863 0.01672 0.00943 -0.0145 0.0328 1.0000 9.000 1.0025 0.01713 0.00984 -0.0125 0.0312 1.0000 9.250 1.0195 0.01754 0.01029 -0.0107 0.0300 1.0000 9.500 1.0370 0.01796 0.01075 -0.0091 0.0287 1.0000 9.750 1.0546 0.01842 0.01123 -0.0075 0.0275 1.0000 10.000 1.0715 0.01895 0.01177 -0.0059 0.0264 1.0000 10.250 1.0884 0.01949 0.01235 -0.0043 0.0255 1.0000 10.500 1.1058 0.02000 0.01292 -0.0028 0.0245 1.0000 10.750 1.1228 0.02055 0.01351 -0.0014 0.0236 1.0000 11.000 1.1393 0.02115 0.01414 0.0001 0.0227 1.0000 11.250 1.1539 0.02188 0.01490 0.0018 0.0219 1.0000 11.500 1.1698 0.02252 0.01561 0.0033 0.0213 1.0000 11.750 1.1851 0.02322 0.01638 0.0048 0.0207 1.0000 12.000 1.1997 0.02396 0.01718 0.0063 0.0202 1.0000 12.250 1.2139 0.02473 0.01802 0.0079 0.0196 1.0000 12.500 1.2272 0.02557 0.01892 0.0094 0.0192 1.0000 12.750 1.2392 0.02651 0.01991 0.0111 0.0187 1.0000 13.000 1.2489 0.02763 0.02108 0.0129 0.0183 1.0000 13.250 1.2601 0.02865 0.02219 0.0144 0.0180 1.0000 13.500 1.2707 0.02973 0.02338 0.0160 0.0177 1.0000 13.750 1.2806 0.03090 0.02463 0.0175 0.0174 1.0000 14.000 1.2896 0.03213 0.02596 0.0190 0.0170 1.0000 14.250 1.2980 0.03344 0.02736 0.0204 0.0167 1.0000 14.500 1.3058 0.03483 0.02884 0.0217 0.0164 1.0000 14.750 1.3125 0.03635 0.03045 0.0229 0.0161 1.0000 15.000 1.3177 0.03803 0.03221 0.0241 0.0158 1.0000 15.250 1.3212 0.03992 0.03419 0.0252 0.0156 1.0000 15.500 1.3227 0.04208 0.03644 0.0261 0.0154 1.0000 15.750 1.3215 0.04458 0.03904 0.0269 0.0152 1.0000 16.000 1.3196 0.04731 0.04188 0.0274 0.0151 1.0000 16.250 1.3188 0.05007 0.04478 0.0276 0.0150 1.0000 16.500 1.3165 0.05314 0.04799 0.0275 0.0148 1.0000 16.750 1.3125 0.05658 0.05157 0.0271 0.0147 1.0000 17.000 1.3068 0.06041 0.05555 0.0263 0.0146 1.0000 17.250 1.2993 0.06472 0.06000 0.0250 0.0145 1.0000 17.500 1.2895 0.06953 0.06497 0.0233 0.0144 1.0000 17.750 1.2775 0.07494 0.07053 0.0210 0.0143 1.0000 18.000 1.2630 0.08102 0.07676 0.0182 0.0143 1.0000 18.250 1.2457 0.08781 0.08372 0.0149 0.0142 1.0000 18.500 1.2254 0.09535 0.09142 0.0110 0.0142 1.0000 18.750 1.2024 0.10363 0.09986 0.0066 0.0142 1.0000 19.000 1.1767 0.11261 0.10901 0.0018 0.0141 1.0000 19.250 1.1493 0.12209 0.11865 -0.0034 0.0141 1.0000