XFOIL Version 6.96 Calculated polar for: St. CYR 234 (Bartel 17-IC) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0184 0.02469 0.02085 -0.1751 0.9770 0.0645 -19.500 -0.9974 0.02368 0.01976 -0.1761 0.9727 0.0655 -19.250 -0.9699 0.02294 0.01893 -0.1773 0.9698 0.0664 -19.000 -0.9403 0.02211 0.01799 -0.1790 0.9677 0.0671 -18.750 -0.9112 0.02106 0.01692 -0.1809 0.9654 0.0681 -18.500 -0.8771 0.02055 0.01639 -0.1825 0.9631 0.0689 -18.250 -0.8594 0.02015 0.01595 -0.1811 0.9564 0.0695 -18.000 -0.8355 0.01977 0.01552 -0.1806 0.9517 0.0702 -17.750 -0.8092 0.01940 0.01509 -0.1805 0.9479 0.0710 -17.500 -0.7898 0.01912 0.01474 -0.1791 0.9433 0.0717 -17.250 -0.7726 0.01883 0.01439 -0.1772 0.9384 0.0723 -17.000 -0.7515 0.01859 0.01406 -0.1759 0.9342 0.0728 -16.750 -0.7279 0.01837 0.01376 -0.1750 0.9304 0.0732 -16.500 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-0.1142 0.5775 0.2938 -1.500 0.7523 0.00812 0.00246 -0.1126 0.5665 0.3026 -1.250 0.7690 0.00821 0.00250 -0.1102 0.5492 0.3088 -1.000 0.7758 0.00848 0.00261 -0.1059 0.5056 0.3151 -0.750 0.7699 0.00923 0.00301 -0.0993 0.4353 0.3200 -0.500 0.7784 0.00971 0.00333 -0.0956 0.4046 0.3264 -0.250 0.7940 0.01002 0.00356 -0.0933 0.3861 0.3325 0.000 0.8095 0.01029 0.00379 -0.0909 0.3672 0.3418 0.250 0.8262 0.01056 0.00400 -0.0889 0.3491 0.3493 0.500 0.8414 0.01086 0.00423 -0.0866 0.3278 0.3582 0.750 0.8531 0.01127 0.00453 -0.0837 0.2989 0.3681 1.000 0.8634 0.01173 0.00487 -0.0807 0.2712 0.3799 1.250 0.8768 0.01208 0.00518 -0.0782 0.2556 0.3966 1.500 0.8901 0.01221 0.00555 -0.0757 0.2455 0.4891 1.750 0.9068 0.01254 0.00592 -0.0739 0.2382 0.5515 2.000 0.9236 0.01288 0.00625 -0.0721 0.2320 0.5659 2.250 0.9427 0.01314 0.00651 -0.0707 0.2287 0.5742 2.500 0.9609 0.01343 0.00680 -0.0692 0.2248 0.5813 2.750 0.9783 0.01378 0.00713 -0.0677 0.2206 0.5869 3.000 0.9936 0.01417 0.00750 -0.0658 0.2158 0.5922 3.250 1.0131 0.01441 0.00778 -0.0646 0.2137 0.5981 3.500 1.0326 0.01468 0.00806 -0.0634 0.2110 0.6033 3.750 1.0509 0.01500 0.00838 -0.0621 0.2078 0.6082 4.000 1.0670 0.01535 0.00875 -0.0605 0.2046 0.6153 4.250 1.0828 0.01576 0.00917 -0.0589 0.2011 0.6212 4.500 1.0999 0.01615 0.00956 -0.0576 0.1982 0.6254 4.750 1.1194 0.01641 0.00987 -0.0566 0.1966 0.6302 5.000 1.1378 0.01673 0.01024 -0.0554 0.1942 0.6351 5.250 1.1555 0.01709 0.01062 -0.0543 0.1913 0.6404 5.500 1.1721 0.01750 0.01105 -0.0530 0.1879 0.6499 5.750 1.1842 0.01789 0.01162 -0.0510 0.1839 0.7091 6.000 1.3220 0.01823 0.01250 -0.0752 0.1755 1.0000 6.250 1.3392 0.01879 0.01302 -0.0742 0.1701 1.0000 6.500 1.3577 0.01929 0.01352 -0.0735 0.1655 1.0000 6.750 1.3748 0.01987 0.01408 -0.0726 0.1587 1.0000 7.000 1.3908 0.02053 0.01470 -0.0716 0.1516 1.0000 7.250 1.4047 0.02131 0.01540 -0.0704 0.1415 1.0000 7.500 1.4178 0.02216 0.01621 -0.0692 0.1325 1.0000 7.750 1.4304 0.02305 0.01705 -0.0679 0.1247 1.0000 8.000 1.4417 0.02406 0.01802 -0.0666 0.1181 1.0000 8.250 1.4551 0.02494 0.01890 -0.0656 0.1137 1.0000 8.500 1.4668 0.02596 0.01988 -0.0644 0.1092 1.0000 8.750 1.4799 0.02690 0.02084 -0.0634 0.1060 1.0000 9.000 1.4930 0.02786 0.02180 -0.0625 0.1029 1.0000 9.250 1.5038 0.02901 0.02294 -0.0615 0.0997 1.0000 9.500 1.5165 0.03003 0.02398 -0.0607 0.0971 1.0000 9.750 1.5298 0.03102 0.02499 -0.0600 0.0947 1.0000 10.000 1.5407 0.03222 0.02620 -0.0591 0.0923 1.0000 10.250 1.5504 0.03352 0.02750 -0.0582 0.0897 1.0000 10.500 1.5630 0.03463 0.02865 -0.0576 0.0880 1.0000 10.750 1.5752 0.03578 0.02982 -0.0570 0.0861 1.0000 11.000 1.5856 0.03707 0.03113 -0.0563 0.0842 1.0000 11.250 1.5936 0.03860 0.03266 -0.0555 0.0821 1.0000 11.500 1.6029 0.04003 0.03413 -0.0549 0.0805 1.0000 11.750 1.6141 0.04135 0.03549 -0.0545 0.0792 1.0000 12.000 1.6243 0.04274 0.03691 -0.0540 0.0776 1.0000 12.250 1.6320 0.04437 0.03857 -0.0535 0.0762 1.0000 12.500 1.6382 0.04615 0.04036 -0.0529 0.0746 1.0000 12.750 1.6420 0.04820 0.04245 -0.0522 0.0732 1.0000 13.000 1.6517 0.04971 0.04402 -0.0520 0.0723 1.0000 13.250 1.6599 0.05138 0.04575 -0.0517 0.0715 1.0000 13.500 1.6660 0.05328 0.04769 -0.0514 0.0705 1.0000 13.750 1.6718 0.05520 0.04965 -0.0511 0.0694 1.0000 14.000 1.6746 0.05747 0.05196 -0.0508 0.0685 1.0000 14.250 1.6772 0.05978 0.05432 -0.0505 0.0676 1.0000 14.500 1.6739 0.06280 0.05738 -0.0502 0.0666 1.0000 14.750 1.6785 0.06495 0.05961 -0.0501 0.0659 1.0000 15.000 1.6819 0.06730 0.06202 -0.0501 0.0653 1.0000 15.250 1.6858 0.06957 0.06435 -0.0502 0.0646 1.0000 15.500 1.6864 0.07228 0.06713 -0.0503 0.0638 1.0000 15.750 1.6877 0.07492 0.06983 -0.0504 0.0631 1.0000 16.000 1.6850 0.07811 0.07308 -0.0507 0.0625 1.0000 16.250 1.6812 0.08146 0.07649 -0.0510 0.0618 1.0000 16.500 1.6752 0.08512 0.08021 -0.0515 0.0610 1.0000 16.750 1.6635 0.08960 0.08477 -0.0521 0.0602 1.0000