XFOIL Version 6.94 Calculated polar for: LOCKHEED C-5A BL1256 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.1938 0.00832 0.00332 -0.0445 0.7989 0.7660 0.500 0.2451 0.00845 0.00351 -0.0425 0.7803 0.8123 1.000 0.2962 0.00853 0.00359 -0.0405 0.7571 0.8418 1.500 0.3463 0.00858 0.00359 -0.0383 0.7287 0.8689 2.000 0.3937 0.00859 0.00359 -0.0354 0.7006 0.8969 2.500 0.4383 0.00853 0.00354 -0.0319 0.6661 0.9268 3.000 0.4876 0.00851 0.00343 -0.0297 0.6202 0.9552 3.500 0.5519 0.00878 0.00343 -0.0311 0.5446 0.9762 4.000 0.6154 0.01044 0.00390 -0.0339 0.2847 0.9986 4.500 0.6503 0.01224 0.00483 -0.0315 0.1356 1.0000 5.000 0.6988 0.01340 0.00570 -0.0308 0.0955 1.0000 5.500 0.7476 0.01458 0.00676 -0.0299 0.0830 1.0000 6.000 0.7955 0.01582 0.00794 -0.0289 0.0764 1.0000 6.500 0.8438 0.01702 0.00908 -0.0279 0.0715 1.0000 7.500 0.9409 0.01937 0.01148 -0.0259 0.0620 1.0000 8.000 0.9885 0.02071 0.01277 -0.0249 0.0584 1.0000 9.000 1.0819 0.02409 0.01631 -0.0227 0.0513 1.0000 9.500 1.1269 0.02582 0.01818 -0.0215 0.0479 1.0000 10.000 1.1697 0.02851 0.02112 -0.0200 0.0450 1.0000 10.500 1.2112 0.03093 0.02371 -0.0185 0.0427 1.0000 11.000 1.2451 0.03471 0.02787 -0.0163 0.0410 1.0000 11.500 1.2646 0.03912 0.03293 -0.0126 0.0395 1.0000 12.000 1.2756 0.04377 0.03807 -0.0085 0.0386 1.0000 12.500 1.2933 0.04699 0.04140 -0.0053 0.0376 1.0000 13.000 1.2839 0.05254 0.04727 -0.0007 0.0369 1.0000 13.500 1.2371 0.06032 0.05567 0.0030 0.0367 1.0000 14.000 1.1850 0.07113 0.06699 0.0016 0.0366 1.0000 14.500 1.1336 0.08450 0.08073 -0.0040 0.0368 1.0000 16.500 0.8733 0.19938 0.19625 -0.0741 0.0427 1.0000 17.000 0.8825 0.20818 0.20505 -0.0791 0.0409 1.0000 17.500 0.8959 0.21546 0.21234 -0.0835 0.0380 1.0000 18.500 0.9210 0.23168 0.22856 -0.0937 0.0344 1.0000 19.000 0.9382 0.23759 0.23449 -0.0968 0.0331 1.0000 19.500 0.9537 0.24486 0.24176 -0.1007 0.0324 1.0000 20.000 0.9661 0.25308 0.24998 -0.1075 0.0298 1.0000 20.500 0.9839 0.25857 0.25550 -0.1105 0.0288 1.0000 21.000 0.9970 0.26694 0.26387 -0.1168 0.0279 1.0000 21.500 1.0127 0.27376 0.27071 -0.1219 0.0258 1.0000 22.500 1.0439 0.28752 0.28449 -0.1319 0.0231 1.0000 23.000 1.0601 0.29320 0.29018 -0.1362 0.0217 1.0000 23.500 1.0774 0.29890 0.29590 -0.1385 0.0212 1.0000 24.000 1.0913 0.30698 0.30398 -0.1468 0.0192 1.0000 24.500 1.1069 0.31233 0.30935 -0.1512 0.0183 1.0000 25.000 1.1225 0.31813 0.31516 -0.1545 0.0180 1.0000 25.500 1.1375 0.32588 0.32292 -0.1622 0.0168 1.0000 26.000 1.1527 0.33159 0.32864 -0.1672 0.0159 1.0000 26.500 1.1673 0.33664 0.33372 -0.1718 0.0153 1.0000 27.500 1.1960 0.34866 0.34576 -0.1824 0.0148 1.0000 28.000 1.2110 0.35500 0.35213 -0.1883 0.0141 1.0000 28.500 1.2250 0.36048 0.35763 -0.1936 0.0134 1.0000 29.000 1.2384 0.36557 0.36275 -0.1988 0.0129 1.0000 29.500 1.2513 0.37033 0.36753 -0.2039 0.0126 1.0000 30.000 1.2636 0.37498 0.37221 -0.2086 0.0123 1.0000 31.000 1.2884 0.38567 0.38295 -0.2199 0.0121 1.0000 31.500 1.3012 0.39104 0.38834 -0.2259 0.0120 1.0000 32.000 1.3135 0.39626 0.39359 -0.2317 0.0116 1.0000 32.500 1.3249 0.40100 0.39837 -0.2372 0.0112 1.0000 33.000 1.3358 0.40561 0.40301 -0.2428 0.0109 1.0000 33.500 1.3463 0.41000 0.40743 -0.2484 0.0105 1.0000 34.000 1.3563 0.41422 0.41169 -0.2540 0.0102 1.0000 34.500 1.3656 0.41816 0.41566 -0.2594 0.0100 1.0000 35.000 1.3738 0.42172 0.41926 -0.2645 0.0098 1.0000 36.000 1.3924 0.42991 0.42752 -0.2765 0.0096 1.0000 36.500 1.4026 0.43433 0.43198 -0.2827 0.0092 1.0000 37.000 1.4112 0.43794 0.43562 -0.2885 0.0084 1.0000 37.500 1.4185 0.44080 0.43852 -0.2942 0.0077 1.0000 38.000 1.4241 0.44312 0.44088 -0.2995 0.0074 1.0000 38.500 1.4346 0.44829 0.44607 -0.3061 0.0069 1.0000 39.000 1.4416 0.45148 0.44930 -0.3120 0.0059 1.0000 39.500 1.4463 0.45351 0.45137 -0.3176 0.0055 1.0000 40.000 1.4545 0.45793 0.45580 -0.3238 0.0052 1.0000 41.500 0.7841 0.47449 0.47296 -0.1696 0.0036 1.0000 42.000 0.7825 0.48037 0.47888 -0.1719 0.0033 1.0000 42.500 0.7805 0.48560 0.48413 -0.1742 0.0030 1.0000 43.000 0.7782 0.49048 0.48904 -0.1766 0.0027 1.0000 43.500 0.7756 0.49497 0.49356 -0.1789 0.0025 1.0000 44.000 0.7726 0.49904 0.49767 -0.1813 0.0023 1.0000 45.500 0.7627 0.51288 0.51159 -0.1881 0.0021 1.0000 46.000 0.7593 0.51735 0.51610 -0.1902 0.0020 1.0000 46.500 0.7555 0.52149 0.52027 -0.1924 0.0018 1.0000 47.000 0.7514 0.52527 0.52408 -0.1946 0.0016 1.0000 47.500 0.7470 0.52866 0.52750 -0.1968 0.0014 1.0000 48.000 0.7423 0.53162 0.53050 -0.1990 0.0012 1.0000 48.500 0.7372 0.53407 0.53297 -0.2013 0.0011 1.0000 50.000 0.7219 0.54369 0.54268 -0.2073 0.0011 1.0000 50.500 0.7166 0.54654 0.54556 -0.2093 0.0010 1.0000 51.000 0.7110 0.54906 0.54810 -0.2112 0.0009 1.0000 51.500 0.7051 0.55126 0.55034 -0.2132 0.0007 1.0000 52.000 0.6990 0.55299 0.55210 -0.2152 0.0006 1.0000 52.500 0.6926 0.55413 0.55327 -0.2172 0.0005 1.0000 53.500 0.6796 0.55769 0.55687 -0.2209 0.0003 1.0000 54.000 0.6731 0.55928 0.55848 -0.2226 0.0003 1.0000 54.500 0.6662 0.56006 0.55930 -0.2245 0.0002 1.0000 55.500 0.6519 0.56168 0.56096 -0.2279 0.0001 1.0000 56.000 0.6446 0.56216 0.56147 -0.2296 0.0001 1.0000 56.500 0.6370 0.56196 0.56130 -0.2313 0.0000 1.0000 58.000 0.6136 0.56083 0.56023 -0.2362 0.0000 1.0000 58.500 0.6056 0.56026 0.55968 -0.2377 0.0000 1.0000 59.000 0.5975 0.55933 0.55878 -0.2393 0.0000 1.0000 59.500 0.5892 0.55810 0.55758 -0.2408 0.0000 1.0000 60.000 0.5808 0.55649 0.55599 -0.2423 0.0001 1.0000