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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9991 0.02057 0.01631 -0.1867 0.9491 0.0571 -19.500 -0.9735 0.01987 0.01553 -0.1872 0.9436 0.0588 -19.250 -0.9575 0.01929 0.01487 -0.1859 0.9359 0.0599 -19.000 -0.9402 0.01874 0.01424 -0.1846 0.9293 0.0607 -18.750 -0.9279 0.01834 0.01381 -0.1821 0.9227 0.0615 -18.500 -0.9127 0.01798 0.01339 -0.1800 0.9159 0.0622 -18.250 -0.8934 0.01764 0.01299 -0.1784 0.9103 0.0630 -18.000 -0.8750 0.01730 0.01259 -0.1767 0.9061 0.0637 -17.750 -0.8561 0.01698 0.01223 -0.1749 0.9024 0.0644 -17.500 -0.8364 0.01666 0.01185 -0.1733 0.8985 0.0650 -17.250 -0.8155 0.01636 0.01149 -0.1718 0.8947 0.0655 -17.000 -0.7938 0.01608 0.01114 -0.1704 0.8910 0.0659 -16.750 -0.7716 0.01582 0.01081 -0.1690 0.8876 0.0662 -16.500 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0.00247 -0.1260 0.6217 0.0853 -6.000 0.2946 0.00902 0.00241 -0.1253 0.6169 0.0861 -5.750 0.3201 0.00900 0.00237 -0.1245 0.6119 0.0869 -5.500 0.3456 0.00898 0.00233 -0.1237 0.6077 0.0876 -5.250 0.3724 0.00892 0.00228 -0.1231 0.6044 0.0890 -5.000 0.3985 0.00886 0.00224 -0.1225 0.5992 0.0910 -4.750 0.4237 0.00883 0.00221 -0.1217 0.5936 0.0932 -4.500 0.4481 0.00882 0.00219 -0.1207 0.5882 0.0959 -4.250 0.4739 0.00876 0.00217 -0.1200 0.5837 0.1019 -4.000 0.4986 0.00870 0.00216 -0.1191 0.5759 0.1139 -3.750 0.5207 0.00870 0.00216 -0.1178 0.5648 0.1258 -3.500 0.5415 0.00874 0.00218 -0.1161 0.5477 0.1352 -3.250 0.5495 0.00899 0.00223 -0.1120 0.4932 0.1401 -3.000 0.5489 0.00954 0.00246 -0.1063 0.4237 0.1445 -2.750 0.5658 0.00974 0.00258 -0.1040 0.4043 0.1497 -2.500 0.5844 0.00990 0.00269 -0.1020 0.3910 0.1539 -2.250 0.6049 0.01000 0.00278 -0.1004 0.3797 0.1601 -2.000 0.6249 0.01015 0.00290 -0.0988 0.3690 0.1652 -1.750 0.6452 0.01027 0.00302 -0.0972 0.3573 0.1731 -1.500 0.6644 0.01042 0.00315 -0.0955 0.3455 0.1826 -1.250 0.6823 0.01059 0.00331 -0.0935 0.3297 0.1987 -1.000 0.6992 0.01079 0.00350 -0.0914 0.3103 0.2227 -0.750 0.7124 0.01113 0.00375 -0.0887 0.2811 0.2389 -0.250 0.7415 0.01177 0.00427 -0.0838 0.2418 0.2660 0.000 0.7597 0.01200 0.00448 -0.0821 0.2336 0.2747 0.250 0.7791 0.01218 0.00468 -0.0806 0.2283 0.2864 0.500 0.7977 0.01242 0.00490 -0.0789 0.2221 0.2931 0.750 0.8164 0.01264 0.00513 -0.0773 0.2167 0.3004 1.000 0.8361 0.01283 0.00534 -0.0760 0.2134 0.3078 1.250 0.8560 0.01304 0.00555 -0.0746 0.2105 0.3137 1.500 0.8753 0.01326 0.00578 -0.0732 0.2075 0.3214 1.750 0.8933 0.01352 0.00605 -0.0716 0.2036 0.3307 2.000 0.9114 0.01379 0.00633 -0.0701 0.1996 0.3401 2.250 0.9315 0.01397 0.00657 -0.0689 0.1984 0.3569 2.500 0.9514 0.01415 0.00681 -0.0677 0.1969 0.3723 2.750 0.9703 0.01439 0.00709 -0.0664 0.1943 0.3864 3.000 0.9881 0.01461 0.00739 -0.0650 0.1916 0.4142 3.250 1.0040 0.01480 0.00783 -0.0632 0.1882 0.5307 3.500 1.0217 0.01517 0.00818 -0.0618 0.1838 0.5454 3.750 1.0406 0.01547 0.00852 -0.0606 0.1821 0.5557 4.000 1.0598 0.01578 0.00884 -0.0595 0.1799 0.5615 4.250 1.0785 0.01610 0.00918 -0.0583 0.1768 0.5673 4.500 1.0965 0.01647 0.00954 -0.0571 0.1729 0.5727 4.750 1.1130 0.01691 0.00996 -0.0558 0.1688 0.5762 5.000 1.1307 0.01730 0.01036 -0.0546 0.1659 0.5797 5.250 1.1484 0.01769 0.01075 -0.0534 0.1616 0.5823 5.500 1.1645 0.01817 0.01120 -0.0521 0.1553 0.5844 5.750 1.1801 0.01868 0.01170 -0.0508 0.1491 0.5868 6.000 1.1929 0.01933 0.01229 -0.0491 0.1389 0.5892 6.250 1.2052 0.02004 0.01294 -0.0474 0.1284 0.5912 6.500 1.2179 0.02075 0.01361 -0.0459 0.1210 0.5929 7.000 1.2450 0.02211 0.01495 -0.0431 0.1109 0.5966 7.250 1.2570 0.02289 0.01572 -0.0417 0.1064 0.5993 7.500 1.2716 0.02356 0.01640 -0.0405 0.1034 0.6016 7.750 1.2855 0.02428 0.01713 -0.0394 0.1004 0.6037 8.000 1.2980 0.02510 0.01795 -0.0382 0.0976 0.6055 8.250 1.3123 0.02584 0.01870 -0.0372 0.0953 0.6074 8.750 1.3390 0.02745 0.02036 -0.0352 0.0905 0.6149 9.000 1.3518 0.02832 0.02124 -0.0342 0.0884 0.6178 9.250 1.3650 0.02918 0.02213 -0.0333 0.0864 0.6220 9.750 1.3908 0.03081 0.02399 -0.0316 0.0828 0.6831 10.250 1.5331 0.03395 0.02773 -0.0556 0.0755 0.9991 10.500 1.5542 0.03531 0.02911 -0.0570 0.0734 1.0000 10.750 1.5651 0.03658 0.03038 -0.0564 0.0718 1.0000 11.000 1.5769 0.03777 0.03160 -0.0558 0.0705 1.0000 11.250 1.5880 0.03905 0.03292 -0.0553 0.0693 1.0000 11.500 1.5991 0.04033 0.03423 -0.0548 0.0679 1.0000 11.750 1.6085 0.04179 0.03571 -0.0543 0.0665 1.0000 12.000 1.6170 0.04334 0.03728 -0.0537 0.0651 1.0000 12.250 1.6261 0.04485 0.03882 -0.0533 0.0640 1.0000 12.500 1.6350 0.04641 0.04042 -0.0529 0.0632 1.0000 12.750 1.6441 0.04794 0.04199 -0.0525 0.0622 1.0000 13.000 1.6515 0.04967 0.04377 -0.0522 0.0613 1.0000 13.250 1.6586 0.05144 0.04558 -0.0518 0.0604 1.0000 13.500 1.6649 0.05331 0.04748 -0.0515 0.0596 1.0000 13.750 1.6693 0.05540 0.04961 -0.0512 0.0587 1.0000 14.000 1.6744 0.05741 0.05166 -0.0509 0.0579 1.0000 14.250 1.6785 0.05958 0.05390 -0.0508 0.0574 1.0000 14.500 1.6844 0.06157 0.05594 -0.0507 0.0569 1.0000 14.750 1.6879 0.06386 0.05829 -0.0506 0.0562 1.0000 15.000 1.6913 0.06616 0.06065 -0.0506 0.0555 1.0000 15.250 1.6928 0.06871 0.06325 -0.0506 0.0548 1.0000 15.500 1.6935 0.07135 0.06596 -0.0506 0.0541 1.0000 15.750 1.6919 0.07434 0.06900 -0.0508 0.0534 1.0000 16.000 1.6903 0.07736 0.07208 -0.0510 0.0527 1.0000 16.250 1.6863 0.08074 0.07553 -0.0513 0.0523 1.0000 16.500 1.6814 0.08427 0.07914 -0.0517 0.0517 1.0000 16.750 1.6796 0.08745 0.08240 -0.0523 0.0513 1.0000 17.000 1.6755 0.09099 0.08602 -0.0530 0.0510 1.0000 17.250 1.6700 0.09477 0.08990 -0.0538 0.0507 1.0000 17.500 1.6636 0.09871 0.09392 -0.0547 0.0500 1.0000 17.750 1.6559 0.10283 0.09813 -0.0558 0.0497 1.0000 18.000 1.6464 0.10725 0.10264 -0.0570 0.0492 1.0000 18.250 1.6370 0.11168 0.10715 -0.0583 0.0488 1.0000 18.500 1.6272 0.11619 0.11175 -0.0598 0.0484 1.0000 18.750 1.6154 0.12102 0.11667 -0.0614 0.0483 1.0000 19.000 1.6033 0.12591 0.12165 -0.0632 0.0480 1.0000