XFOIL Version 6.96 Calculated polar for: LOCKHEED C-5A BL758.6 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.5721 0.08660 0.08258 -0.0457 1.0000 0.0223 -10.500 -0.6443 0.06518 0.06112 -0.0594 1.0000 0.0213 -10.250 -0.7006 0.05740 0.05316 -0.0601 1.0000 0.0210 -10.000 -0.7438 0.05411 0.04974 -0.0544 1.0000 0.0209 -9.750 -0.7797 0.04983 0.04521 -0.0491 1.0000 0.0207 -9.500 -0.8051 0.04560 0.04064 -0.0442 1.0000 0.0206 -9.250 -0.8191 0.04188 0.03654 -0.0401 1.0000 0.0205 -9.000 -0.8161 0.03822 0.03246 -0.0385 0.9985 0.0206 -8.750 -0.7999 0.03500 0.02880 -0.0388 0.9959 0.0207 -8.500 -0.7804 0.03246 0.02588 -0.0390 0.9938 0.0209 -8.250 -0.7601 0.03035 0.02345 -0.0388 0.9913 0.0211 -8.000 -0.7369 0.02849 0.02130 -0.0390 0.9890 0.0214 -7.750 -0.7116 0.02685 0.01938 -0.0394 0.9870 0.0218 -7.500 -0.6849 0.02540 0.01769 -0.0399 0.9855 0.0223 -7.250 -0.6600 0.02414 0.01621 -0.0399 0.9834 0.0228 -7.000 -0.6350 0.02301 0.01490 -0.0398 0.9808 0.0234 -6.750 -0.6081 0.02198 0.01372 -0.0400 0.9785 0.0240 -6.500 -0.5805 0.02110 0.01281 -0.0406 0.9767 0.0248 -6.250 -0.5510 0.02039 0.01207 -0.0414 0.9750 0.0259 -6.000 -0.5236 0.01972 0.01132 -0.0417 0.9728 0.0272 -5.750 -0.4983 0.01916 0.01066 -0.0415 0.9694 0.0290 -5.500 -0.4703 0.01853 0.01004 -0.0420 0.9667 0.0312 -5.250 -0.4395 0.01804 0.00951 -0.0429 0.9645 0.0341 -5.000 -0.4076 0.01746 0.00887 -0.0441 0.9627 0.0372 -4.750 -0.3814 0.01702 0.00843 -0.0441 0.9590 0.0409 -4.500 -0.3549 0.01658 0.00796 -0.0440 0.9553 0.0457 -4.250 -0.3252 0.01615 0.00754 -0.0447 0.9527 0.0516 -4.000 -0.2937 0.01570 0.00711 -0.0458 0.9506 0.0587 -3.750 -0.2611 0.01528 0.00674 -0.0470 0.9490 0.0705 -3.500 -0.2372 0.01494 0.00648 -0.0465 0.9446 0.0888 -3.250 -0.2103 0.01459 0.00627 -0.0465 0.9407 0.1201 -3.000 -0.1796 0.01422 0.00602 -0.0474 0.9379 0.1516 -2.750 -0.1471 0.01381 0.00579 -0.0487 0.9358 0.1960 -2.500 -0.1138 0.01322 0.00554 -0.0503 0.9340 0.2753 -2.250 -0.0955 0.01244 0.00537 -0.0489 0.9277 0.4212 -2.000 -0.0701 0.01173 0.00537 -0.0485 0.9239 0.5925 -1.750 -0.0400 0.01146 0.00540 -0.0487 0.9213 0.6790 -1.500 -0.0079 0.01131 0.00537 -0.0492 0.9193 0.7284 -1.250 0.0152 0.01128 0.00540 -0.0480 0.9133 0.7555 -1.000 0.0430 0.01121 0.00538 -0.0477 0.9090 0.7808 -0.750 0.0739 0.01111 0.00532 -0.0480 0.9060 0.8032 -0.500 0.1057 0.01101 0.00526 -0.0483 0.9037 0.8256 -0.250 0.1267 0.01103 0.00533 -0.0466 0.8964 0.8463 0.000 0.1558 0.01096 0.00529 -0.0465 0.8923 0.8642 0.250 0.1877 0.01086 0.00521 -0.0469 0.8893 0.8813 0.500 0.2121 0.01084 0.00522 -0.0458 0.8815 0.8965 1.000 0.2757 0.01058 0.00500 -0.0466 0.8675 0.9182 1.250 0.3097 0.01044 0.00487 -0.0476 0.8603 0.9274 1.500 0.3427 0.01028 0.00471 -0.0483 0.8470 0.9356 1.750 0.3785 0.01002 0.00442 -0.0493 0.8278 0.9437 2.000 0.4125 0.00990 0.00427 -0.0502 0.8040 0.9510 2.250 0.4474 0.00980 0.00411 -0.0513 0.7771 0.9588 2.500 0.4840 0.00975 0.00391 -0.0527 0.7322 0.9642 2.750 0.5167 0.00989 0.00378 -0.0534 0.6743 0.9711 3.000 0.5475 0.01022 0.00380 -0.0539 0.6099 0.9780 3.250 0.5752 0.01074 0.00394 -0.0539 0.5288 0.9861 3.500 0.6016 0.01147 0.00418 -0.0541 0.4260 0.9944 3.750 0.6233 0.01228 0.00450 -0.0535 0.3283 1.0000 4.000 0.6341 0.01290 0.00477 -0.0504 0.2622 1.0000 4.250 0.6472 0.01349 0.00507 -0.0479 0.2020 1.0000 4.500 0.6630 0.01401 0.00538 -0.0457 0.1676 1.0000 4.750 0.6810 0.01446 0.00568 -0.0440 0.1354 1.0000 5.000 0.6998 0.01493 0.00602 -0.0425 0.1149 1.0000 5.250 0.7197 0.01537 0.00639 -0.0411 0.0988 1.0000 5.500 0.7399 0.01582 0.00679 -0.0398 0.0873 1.0000 5.750 0.7607 0.01625 0.00721 -0.0385 0.0792 1.0000 6.000 0.7809 0.01676 0.00766 -0.0372 0.0727 1.0000 6.250 0.8022 0.01718 0.00813 -0.0361 0.0684 1.0000 6.500 0.8231 0.01765 0.00861 -0.0350 0.0649 1.0000 6.750 0.8432 0.01819 0.00915 -0.0337 0.0623 1.0000 7.000 0.8632 0.01877 0.00974 -0.0324 0.0602 1.0000 7.250 0.8838 0.01930 0.01034 -0.0312 0.0581 1.0000 7.500 0.9042 0.01985 0.01093 -0.0300 0.0560 1.0000 7.750 0.9241 0.02046 0.01157 -0.0288 0.0542 1.0000 8.000 0.9429 0.02119 0.01230 -0.0275 0.0524 1.0000 8.250 0.9620 0.02199 0.01313 -0.0262 0.0506 1.0000 8.500 0.9824 0.02264 0.01388 -0.0251 0.0489 1.0000 8.750 1.0024 0.02333 0.01465 -0.0239 0.0471 1.0000 9.000 1.0214 0.02403 0.01541 -0.0227 0.0452 1.0000 9.250 1.0393 0.02484 0.01624 -0.0214 0.0435 1.0000 9.500 1.0576 0.02598 0.01740 -0.0202 0.0418 1.0000 9.750 1.0762 0.02669 0.01829 -0.0189 0.0402 1.0000 10.000 1.0941 0.02753 0.01926 -0.0175 0.0385 1.0000 10.250 1.1106 0.02833 0.02016 -0.0160 0.0368 1.0000 10.500 1.1257 0.02913 0.02100 -0.0144 0.0354 1.0000 10.750 1.1405 0.03028 0.02219 -0.0129 0.0340 1.0000 11.000 1.1554 0.03123 0.02338 -0.0112 0.0324 1.0000 11.250 1.1689 0.03219 0.02451 -0.0094 0.0308 1.0000 11.500 1.1811 0.03308 0.02551 -0.0076 0.0296 1.0000 11.750 1.1923 0.03401 0.02650 -0.0058 0.0286 1.0000 12.000 1.2021 0.03529 0.02787 -0.0040 0.0277 1.0000 12.250 1.2111 0.03689 0.02975 -0.0020 0.0265 1.0000 12.500 1.2186 0.03837 0.03144 -0.0001 0.0254 1.0000 12.750 1.2255 0.03970 0.03290 0.0018 0.0245 1.0000 13.000 1.2321 0.04094 0.03425 0.0034 0.0237 1.0000 13.250 1.2376 0.04231 0.03567 0.0050 0.0232 1.0000 13.500 1.2389 0.04443 0.03800 0.0067 0.0225 1.0000 13.750 1.2365 0.04711 0.04097 0.0083 0.0217 1.0000 14.000 1.2325 0.04993 0.04403 0.0097 0.0211 1.0000 14.250 1.2272 0.05294 0.04725 0.0107 0.0207 1.0000 14.500 1.2210 0.05616 0.05067 0.0112 0.0203 1.0000 14.750 1.2132 0.05972 0.05442 0.0112 0.0200 1.0000 15.000 1.2041 0.06370 0.05856 0.0106 0.0197 1.0000 15.250 1.1929 0.06823 0.06327 0.0093 0.0195 1.0000 15.500 1.1782 0.07366 0.06889 0.0072 0.0193 1.0000 15.750 1.1593 0.08034 0.07577 0.0040 0.0193 1.0000 16.000 1.1275 0.09021 0.08591 -0.0017 0.0193 1.0000