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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.8536 0.05081 0.04715 -0.1342 0.9881 0.0724 -18.750 -0.8921 0.03936 0.03522 -0.1525 0.9815 0.0733 -18.500 -0.8614 0.03871 0.03468 -0.1532 0.9802 0.0745 -18.250 -0.8289 0.03791 0.03391 -0.1555 0.9789 0.0754 -18.000 -0.8171 0.03563 0.03155 -0.1594 0.9738 0.0763 -17.750 -0.8047 0.03395 0.02978 -0.1616 0.9693 0.0773 -17.500 -0.7893 0.03245 0.02814 -0.1633 0.9663 0.0783 -17.250 -0.7720 0.03088 0.02637 -0.1650 0.9640 0.0794 -17.000 -0.7634 0.02989 0.02519 -0.1640 0.9587 0.0801 -16.750 -0.7494 0.02829 0.02346 -0.1637 0.9544 0.0810 -16.500 -0.7195 0.02744 0.02266 -0.1644 0.9527 0.0820 -16.250 -0.6888 0.02689 0.02211 -0.1652 0.9509 0.0829 -16.000 -0.6589 0.02625 0.02142 -0.1660 0.9491 0.0839 -15.750 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-0.1325 0.7356 0.1197 -6.250 0.2912 0.01053 0.00369 -0.1315 0.7289 0.1230 -6.000 0.3172 0.01044 0.00359 -0.1308 0.7228 0.1273 -5.750 0.3443 0.01036 0.00351 -0.1303 0.7176 0.1340 -5.500 0.3702 0.01026 0.00345 -0.1297 0.7131 0.1431 -5.250 0.3960 0.01017 0.00340 -0.1290 0.7086 0.1538 -5.000 0.4222 0.01011 0.00335 -0.1284 0.7037 0.1646 -4.750 0.4489 0.01003 0.00329 -0.1279 0.6987 0.1758 -4.500 0.4751 0.00998 0.00327 -0.1273 0.6939 0.1869 -4.250 0.4999 0.00991 0.00327 -0.1265 0.6888 0.1990 -4.000 0.5256 0.00985 0.00327 -0.1258 0.6839 0.2148 -3.750 0.5524 0.00984 0.00329 -0.1254 0.6790 0.2342 -3.500 0.5785 0.00983 0.00335 -0.1249 0.6741 0.2538 -3.250 0.6028 0.00982 0.00339 -0.1239 0.6685 0.2702 -3.000 0.6277 0.00983 0.00343 -0.1231 0.6622 0.2848 -2.750 0.6545 0.00989 0.00346 -0.1227 0.6562 0.2970 -2.500 0.6776 0.00989 0.00352 -0.1215 0.6504 0.3082 -2.250 0.7016 0.00989 0.00355 -0.1205 0.6442 0.3186 -2.000 0.7270 0.00995 0.00359 -0.1199 0.6381 0.3290 -1.750 0.7500 0.00995 0.00364 -0.1187 0.6318 0.3390 -1.500 0.7720 0.00996 0.00368 -0.1174 0.6238 0.3488 -1.250 0.7949 0.01001 0.00371 -0.1163 0.6160 0.3585 -1.000 0.8153 0.01000 0.00377 -0.1147 0.6076 0.3685 -0.750 0.8350 0.01003 0.00380 -0.1129 0.5978 0.3785 -0.500 0.8527 0.01002 0.00385 -0.1107 0.5869 0.3905 -0.250 0.8658 0.01002 0.00388 -0.1077 0.5736 0.4065 0.000 0.8756 0.01003 0.00396 -0.1040 0.5535 0.4313 0.500 0.8609 0.01107 0.00475 -0.0903 0.4471 0.5487 0.750 0.8619 0.01178 0.00526 -0.0854 0.4139 0.5679 1.000 0.8704 0.01231 0.00568 -0.0820 0.3916 0.5830 1.250 0.8822 0.01273 0.00604 -0.0792 0.3722 0.5971 1.500 0.8941 0.01318 0.00640 -0.0766 0.3518 0.6081 1.750 0.9046 0.01362 0.00678 -0.0737 0.3284 0.6181 2.000 0.9140 0.01415 0.00720 -0.0708 0.3050 0.6277 2.250 0.9244 0.01461 0.00761 -0.0681 0.2857 0.6403 2.500 0.9354 0.01499 0.00805 -0.0654 0.2729 0.6608 2.750 1.0239 0.01532 0.00894 -0.0793 0.2564 1.0000 3.000 1.0388 0.01588 0.00944 -0.0775 0.2500 1.0000 3.250 1.0575 0.01629 0.00984 -0.0764 0.2451 1.0000 3.500 1.0746 0.01679 0.01031 -0.0750 0.2402 1.0000 3.750 1.0895 0.01740 0.01086 -0.0734 0.2351 1.0000 4.000 1.1071 0.01790 0.01136 -0.0722 0.2311 1.0000 4.250 1.1264 0.01833 0.01180 -0.0714 0.2274 1.0000 4.500 1.1437 0.01886 0.01232 -0.0702 0.2233 1.0000 4.750 1.1594 0.01949 0.01291 -0.0689 0.2193 1.0000 5.000 1.1743 0.02018 0.01357 -0.0676 0.2151 1.0000 5.250 1.1945 0.02060 0.01402 -0.0669 0.2122 1.0000 5.500 1.2129 0.02111 0.01456 -0.0661 0.2087 1.0000 5.750 1.2296 0.02172 0.01516 -0.0651 0.2050 1.0000 6.000 1.2444 0.02246 0.01586 -0.0639 0.2008 1.0000 6.250 1.2611 0.02310 0.01652 -0.0630 0.1971 1.0000 6.500 1.2802 0.02361 0.01708 -0.0624 0.1933 1.0000 6.750 1.2970 0.02426 0.01772 -0.0617 0.1887 1.0000 7.000 1.3105 0.02513 0.01855 -0.0605 0.1840 1.0000 7.250 1.3286 0.02573 0.01919 -0.0600 0.1797 1.0000 7.500 1.3457 0.02639 0.01988 -0.0593 0.1742 1.0000 7.750 1.3582 0.02738 0.02081 -0.0583 0.1681 1.0000 8.000 1.3760 0.02802 0.02150 -0.0578 0.1615 1.0000 8.250 1.3887 0.02903 0.02246 -0.0569 0.1537 1.0000 8.500 1.4026 0.02998 0.02339 -0.0561 0.1457 1.0000 8.750 1.4139 0.03112 0.02449 -0.0552 0.1382 1.0000 9.000 1.4238 0.03239 0.02572 -0.0542 0.1315 1.0000 9.250 1.4341 0.03365 0.02698 -0.0533 0.1261 1.0000 9.500 1.4431 0.03504 0.02835 -0.0523 0.1213 1.0000 9.750 1.4510 0.03653 0.02983 -0.0513 0.1173 1.0000 10.000 1.4612 0.03786 0.03119 -0.0506 0.1137 1.0000 10.250 1.4685 0.03944 0.03277 -0.0497 0.1106 1.0000 10.500 1.4738 0.04123 0.03456 -0.0487 0.1075 1.0000 10.750 1.4846 0.04259 0.03598 -0.0482 0.1050 1.0000 11.000 1.4929 0.04416 0.03758 -0.0476 0.1025 1.0000 11.250 1.4975 0.04609 0.03952 -0.0468 0.1002 1.0000 11.500 1.5008 0.04815 0.04159 -0.0460 0.0979 1.0000 11.750 1.5103 0.04971 0.04323 -0.0457 0.0960 1.0000 12.000 1.5184 0.05140 0.04497 -0.0453 0.0940 1.0000 12.250 1.5233 0.05343 0.04703 -0.0449 0.0922 1.0000 12.500 1.5255 0.05570 0.04931 -0.0443 0.0905 1.0000 12.750 1.5265 0.05813 0.05178 -0.0438 0.0890 1.0000 13.000 1.5340 0.05998 0.05372 -0.0436 0.0877 1.0000 13.250 1.5395 0.06205 0.05585 -0.0435 0.0864 1.0000 13.500 1.5437 0.06427 0.05813 -0.0433 0.0851 1.0000 13.750 1.5469 0.06661 0.06052 -0.0432 0.0839 1.0000 14.000 1.5476 0.06924 0.06319 -0.0431 0.0828 1.0000 14.250 1.5472 0.07198 0.06594 -0.0429 0.0816 1.0000 14.500 1.5478 0.07464 0.06866 -0.0429 0.0806 1.0000 14.750 1.5514 0.07707 0.07119 -0.0431 0.0798 1.0000 15.000 1.5531 0.07975 0.07396 -0.0433 0.0790 1.0000 15.250 1.5550 0.08240 0.07668 -0.0436 0.0781 1.0000 15.500 1.5556 0.08528 0.07963 -0.0440 0.0773 1.0000 15.750 1.5564 0.08811 0.08253 -0.0445 0.0765 1.0000 16.000 1.5562 0.09112 0.08559 -0.0450 0.0758 1.0000 16.250 1.5556 0.09414 0.08865 -0.0456 0.0750 1.0000 16.500 1.5558 0.09696 0.09149 -0.0461 0.0741 1.0000 16.750 1.5584 0.09928 0.09382 -0.0464 0.0732 1.0000 17.000 1.5579 0.10243 0.09708 -0.0472 0.0728 1.0000 17.250 1.5567 0.10571 0.10047 -0.0483 0.0723 1.0000 17.500 1.5558 0.10894 0.10379 -0.0493 0.0717 1.0000 17.750 1.5551 0.11208 0.10701 -0.0503 0.0711 1.0000 18.000 1.5529 0.11555 0.11057 -0.0517 0.0703 1.0000