XFOIL Version 6.96 Calculated polar for: NACA 64(4)-421 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.8404 0.10657 0.10102 -0.0627 1.0000 0.0331 -19.500 -0.8588 0.09987 0.09408 -0.0664 1.0000 0.0333 -19.250 -0.8568 0.09677 0.09097 -0.0679 1.0000 0.0336 -19.000 -0.8557 0.09354 0.08770 -0.0695 1.0000 0.0340 -18.750 -0.8563 0.09008 0.08418 -0.0711 1.0000 0.0343 -18.500 -0.8577 0.08654 0.08054 -0.0727 1.0000 0.0346 -18.250 -0.8587 0.08310 0.07703 -0.0743 1.0000 0.0351 -18.000 -0.8599 0.07974 0.07356 -0.0757 1.0000 0.0355 -17.750 -0.8600 0.07658 0.07028 -0.0769 1.0000 0.0359 -17.500 -0.8594 0.07355 0.06714 -0.0779 1.0000 0.0364 -17.250 -0.8574 0.07077 0.06423 -0.0788 1.0000 0.0368 -17.000 -0.8547 0.06814 0.06147 -0.0795 1.0000 0.0373 -16.750 -0.8507 0.06572 0.05891 -0.0800 1.0000 0.0377 -16.500 -0.8427 0.06389 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0.00652 -0.0647 0.6161 0.5620 -2.000 0.0790 0.01460 0.00641 -0.0651 0.6125 0.5652 -1.750 0.1077 0.01456 0.00628 -0.0654 0.6093 0.5677 -1.500 0.1363 0.01455 0.00624 -0.0657 0.6066 0.5698 -1.250 0.1648 0.01456 0.00623 -0.0659 0.6037 0.5720 -1.000 0.1928 0.01456 0.00626 -0.0661 0.6004 0.5741 -0.750 0.2210 0.01457 0.00626 -0.0664 0.5971 0.5764 -0.500 0.2494 0.01458 0.00625 -0.0667 0.5939 0.5788 -0.250 0.2780 0.01459 0.00622 -0.0670 0.5909 0.5816 0.000 0.3071 0.01461 0.00617 -0.0675 0.5883 0.5846 0.250 0.3365 0.01466 0.00614 -0.0680 0.5861 0.5875 0.500 0.3640 0.01470 0.00625 -0.0681 0.5834 0.5896 0.750 0.3917 0.01475 0.00636 -0.0683 0.5807 0.5919 1.000 0.4197 0.01482 0.00646 -0.0685 0.5780 0.5945 1.250 0.4478 0.01488 0.00654 -0.0687 0.5756 0.5973 1.500 0.4762 0.01495 0.00662 -0.0691 0.5733 0.6004 1.750 0.5050 0.01503 0.00668 -0.0694 0.5712 0.6036 2.000 0.5343 0.01511 0.00672 -0.0699 0.5691 0.6069 2.250 0.5630 0.01520 0.00683 -0.0702 0.5670 0.6096 2.500 0.5895 0.01532 0.00705 -0.0702 0.5645 0.6126 2.750 0.6165 0.01545 0.00726 -0.0703 0.5621 0.6161 3.000 0.6438 0.01558 0.00746 -0.0705 0.5597 0.6201 3.250 0.6715 0.01571 0.00761 -0.0707 0.5571 0.6244 3.500 0.6994 0.01581 0.00774 -0.0709 0.5546 0.6283 3.750 0.7272 0.01591 0.00789 -0.0711 0.5521 0.6316 4.000 0.7560 0.01602 0.00803 -0.0714 0.5498 0.6354 4.250 0.7831 0.01618 0.00825 -0.0715 0.5474 0.6397 4.500 0.8084 0.01637 0.00854 -0.0714 0.5446 0.6443 4.750 0.8343 0.01655 0.00880 -0.0713 0.5417 0.6488 5.000 0.8600 0.01671 0.00907 -0.0712 0.5390 0.6528 5.250 0.8866 0.01686 0.00930 -0.0712 0.5363 0.6573 5.500 0.9143 0.01699 0.00948 -0.0713 0.5337 0.6625 5.750 0.9437 0.01712 0.00961 -0.0718 0.5312 0.6680 6.000 0.9659 0.01731 0.00995 -0.0711 0.5269 0.6724 6.250 0.9874 0.01742 0.01019 -0.0702 0.5210 0.6777 6.500 1.0132 0.01743 0.01024 -0.0699 0.5155 0.6838 6.750 1.0380 0.01751 0.01035 -0.0695 0.5098 0.6900 7.000 1.0554 0.01762 0.01061 -0.0679 0.5017 0.6953 7.250 1.0811 0.01757 0.01054 -0.0675 0.4943 0.7014 7.500 1.0958 0.01781 0.01094 -0.0656 0.4866 0.7081 7.750 1.1155 0.01792 0.01112 -0.0643 0.4797 0.7137 8.000 1.1330 0.01810 0.01141 -0.0628 0.4726 0.7199 8.250 1.1457 0.01833 0.01173 -0.0605 0.4642 0.7269 8.500 1.1568 0.01853 0.01200 -0.0579 0.4552 0.7334 8.750 1.1634 0.01889 0.01245 -0.0547 0.4436 0.7402 9.000 1.1682 0.01943 0.01307 -0.0516 0.4291 0.7482 9.250 1.1711 0.02006 0.01375 -0.0484 0.4099 0.7555 9.500 1.1709 0.02091 0.01456 -0.0450 0.3839 0.7639 9.750 1.1653 0.02216 0.01567 -0.0413 0.3574 0.7726 10.000 1.1570 0.02376 0.01718 -0.0377 0.3313 0.7813 10.250 1.1480 0.02567 0.01898 -0.0346 0.3063 0.7909 10.500 1.1386 0.02772 0.02098 -0.0316 0.2816 0.8000 10.750 1.1289 0.03006 0.02322 -0.0291 0.2586 0.8102 11.000 1.1209 0.03236 0.02548 -0.0269 0.2377 0.8204 11.250 1.1141 0.03475 0.02783 -0.0250 0.2180 0.8317 11.500 1.1087 0.03715 0.03019 -0.0234 0.2002 0.8441 11.750 1.1052 0.03945 0.03249 -0.0219 0.1846 0.8579 12.000 1.1014 0.04182 0.03485 -0.0206 0.1691 0.8749 12.250 1.0990 0.04410 0.03715 -0.0193 0.1552 0.8987 12.500 1.0987 0.04635 0.03944 -0.0187 0.1419 0.9550 13.000 1.1022 0.05118 0.04418 -0.0183 0.1193 1.0000 13.250 1.1052 0.05368 0.04663 -0.0183 0.1095 1.0000 13.500 1.1099 0.05606 0.04900 -0.0184 0.1006 1.0000 13.750 1.1149 0.05843 0.05136 -0.0186 0.0928 1.0000 14.000 1.1191 0.06093 0.05385 -0.0187 0.0860 1.0000 14.250 1.1236 0.06345 0.05635 -0.0190 0.0795 1.0000 14.500 1.1292 0.06586 0.05878 -0.0193 0.0737 1.0000 14.750 1.1338 0.06843 0.06135 -0.0196 0.0686 1.0000 15.000 1.1387 0.07101 0.06395 -0.0200 0.0640 1.0000 15.250 1.1438 0.07360 0.06656 -0.0205 0.0599 1.0000 15.500 1.1477 0.07636 0.06933 -0.0210 0.0563 1.0000 15.750 1.1530 0.07899 0.07201 -0.0215 0.0530 1.0000 16.000 1.1567 0.08185 0.07488 -0.0222 0.0503 1.0000 16.250 1.1617 0.08458 0.07768 -0.0228 0.0478 1.0000 16.500 1.1655 0.08751 0.08064 -0.0236 0.0455 1.0000 16.750 1.1689 0.09049 0.08366 -0.0244 0.0436 1.0000 17.000 1.1734 0.09339 0.08663 -0.0252 0.0418 1.0000 17.250 1.1766 0.09647 0.08976 -0.0262 0.0403 1.0000 17.500 1.1785 0.09976 0.09308 -0.0272 0.0389 1.0000 17.750 1.1830 0.10273 0.09615 -0.0282 0.0375 1.0000 18.000 1.1864 0.10586 0.09935 -0.0294 0.0362 1.0000 18.250 1.1882 0.10924 0.10277 -0.0307 0.0353 1.0000 18.500 1.1903 0.11258 0.10616 -0.0320 0.0343 1.0000 18.750 1.1938 0.11575 0.10942 -0.0332 0.0333 1.0000 19.000 1.1969 0.11899 0.11273 -0.0346 0.0323 1.0000 19.250 1.1991 0.12238 0.11619 -0.0362 0.0314 1.0000