XFOIL Version 6.94 Calculated polar for: DEFIANT CANARD BL110 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 0.3274 0.00965 0.00392 -0.0504 0.5696 0.9169 0.500 0.4101 0.01033 0.00432 -0.0553 0.5434 0.9408 1.000 0.4869 0.01076 0.00452 -0.0598 0.5182 0.9523 1.500 0.5625 0.01114 0.00469 -0.0643 0.4941 0.9626 2.000 0.6360 0.01145 0.00483 -0.0685 0.4730 0.9730 2.500 0.7107 0.01177 0.00497 -0.0732 0.4564 0.9837 3.000 0.7880 0.01195 0.00508 -0.0784 0.4425 0.9933 3.500 0.8560 0.01217 0.00520 -0.0819 0.4323 1.0000 4.000 0.8865 0.01231 0.00535 -0.0777 0.4245 1.0000 4.500 0.9194 0.01261 0.00556 -0.0738 0.4171 1.0000 5.000 0.9556 0.01294 0.00591 -0.0704 0.4104 1.0000 5.500 0.9927 0.01327 0.00627 -0.0672 0.4030 1.0000 6.000 1.0319 0.01375 0.00670 -0.0644 0.3955 1.0000 6.500 1.0719 0.01422 0.00725 -0.0617 0.3887 1.0000 7.000 1.1109 0.01469 0.00779 -0.0589 0.3812 1.0000 7.500 1.1563 0.01546 0.00849 -0.0574 0.3724 1.0000 8.000 1.1925 0.01598 0.00920 -0.0542 0.3652 1.0000 8.500 1.2320 0.01663 0.00992 -0.0516 0.3570 1.0000 9.000 1.2679 0.01737 0.01074 -0.0485 0.3462 1.0000 9.500 1.2910 0.01780 0.01122 -0.0429 0.3339 1.0000 10.000 1.3101 0.01834 0.01192 -0.0367 0.3238 1.0000 10.500 1.3295 0.01886 0.01255 -0.0310 0.3133 1.0000 11.000 1.3489 0.01953 0.01344 -0.0259 0.3011 1.0000 11.500 1.3661 0.02042 0.01447 -0.0211 0.2842 1.0000 12.000 1.3805 0.02190 0.01600 -0.0167 0.2650 1.0000 12.500 1.3822 0.02453 0.01856 -0.0120 0.2381 1.0000 13.000 1.3866 0.02752 0.02159 -0.0083 0.2109 1.0000 13.500 1.3680 0.03263 0.02649 -0.0044 0.1528 1.0000 14.000 1.3360 0.03974 0.03351 -0.0014 0.1177 1.0000 14.500 1.3113 0.04721 0.04100 -0.0003 0.0957 1.0000 15.000 1.2856 0.05557 0.04940 -0.0004 0.0758 1.0000 15.500 1.2514 0.06542 0.05924 -0.0013 0.0528 1.0000 16.000 1.2127 0.07634 0.07011 -0.0031 0.0308 1.0000 16.500 1.1778 0.08734 0.08112 -0.0053 0.0176 1.0000 17.000 1.1609 0.09623 0.09014 -0.0074 0.0147 1.0000 17.500 1.1432 0.10541 0.09947 -0.0097 0.0123 1.0000 18.000 1.1278 0.11445 0.10867 -0.0124 0.0109 1.0000 18.500 1.1193 0.12254 0.11693 -0.0150 0.0102 1.0000 19.000 1.1117 0.13060 0.12514 -0.0178 0.0099 1.0000 19.500 1.1031 0.13891 0.13354 -0.0211 0.0093 1.0000 20.000 1.1043 0.14551 0.14024 -0.0237 0.0090 1.0000 20.500 1.1090 0.15147 0.14633 -0.0263 0.0088 1.0000 21.000 1.1168 0.15675 0.15171 -0.0286 0.0084 1.0000 21.500 1.1268 0.16159 0.15667 -0.0308 0.0083 1.0000 22.000 1.1365 0.16642 0.16163 -0.0331 0.0080 1.0000 22.500 1.1448 0.17162 0.16700 -0.0359 0.0081 1.0000 23.000 1.1482 0.17795 0.17353 -0.0395 0.0080 1.0000 23.500 1.1462 0.18571 0.18155 -0.0442 0.0080 1.0000 24.000 1.1349 0.19614 0.19231 -0.0509 0.0081 1.0000 24.500 1.1153 0.20950 0.20602 -0.0598 0.0084 1.0000 25.000 1.0820 0.22840 0.22530 -0.0721 0.0087 1.0000 25.500 1.0554 0.24725 0.24432 -0.0837 0.0093 1.0000 27.000 0.8011 0.31756 0.31544 -0.1138 0.0193 1.0000 27.500 0.8032 0.32893 0.32683 -0.1186 0.0178 1.0000 28.500 0.8150 0.34702 0.34498 -0.1261 0.0155 1.0000 29.000 0.8213 0.35534 0.35334 -0.1297 0.0143 1.0000 29.500 0.8295 0.36238 0.36042 -0.1326 0.0138 1.0000 30.000 0.8311 0.37486 0.37291 -0.1371 0.0125 1.0000 30.500 0.8365 0.38326 0.38136 -0.1406 0.0118 1.0000 31.000 0.8432 0.39034 0.38847 -0.1435 0.0114 1.0000 31.500 0.8449 0.40280 0.40095 -0.1478 0.0109 1.0000 32.000 0.8492 0.41170 0.40989 -0.1512 0.0097 1.0000 33.000 0.8562 0.43079 0.42903 -0.1580 0.0089 1.0000 33.500 0.8595 0.44055 0.43882 -0.1614 0.0081 1.0000 34.000 0.8624 0.44915 0.44745 -0.1647 0.0076 1.0000 35.000 0.8670 0.46784 0.46619 -0.1712 0.0071 1.0000 35.500 0.8690 0.47809 0.47648 -0.1744 0.0066 1.0000 36.000 0.8707 0.48713 0.48555 -0.1775 0.0062 1.0000 36.500 0.8719 0.49565 0.49410 -0.1806 0.0058 1.0000 37.000 0.8728 0.50364 0.50213 -0.1837 0.0056 1.0000 38.000 0.8736 0.52244 0.52098 -0.1897 0.0053 1.0000 38.500 0.8738 0.53182 0.53039 -0.1926 0.0048 1.0000 39.000 0.8735 0.54023 0.53883 -0.1955 0.0045 1.0000 39.500 0.8728 0.54824 0.54687 -0.1984 0.0042 1.0000 40.000 0.8715 0.55533 0.55400 -0.2012 0.0040 1.0000 41.000 0.8687 0.57313 0.57185 -0.2067 0.0038 1.0000 41.500 0.8671 0.58132 0.58006 -0.2094 0.0037 1.0000 42.000 0.8650 0.58924 0.58801 -0.2120 0.0034 1.0000 42.500 0.8624 0.59646 0.59527 -0.2146 0.0033 1.0000 43.000 0.8596 0.60357 0.60240 -0.2171 0.0031 1.0000 43.500 0.8564 0.61019 0.60906 -0.2196 0.0029 1.0000 44.000 0.8528 0.61646 0.61536 -0.2221 0.0028 1.0000 44.500 0.8486 0.62183 0.62076 -0.2246 0.0026 1.0000 46.000 0.8359 0.64087 0.63987 -0.2315 0.0025 1.0000 46.500 0.8314 0.64689 0.64592 -0.2336 0.0024 1.0000 47.000 0.8264 0.65234 0.65139 -0.2357 0.0022 1.0000 48.000 0.8154 0.66151 0.66062 -0.2399 0.0020 1.0000 48.500 0.8094 0.66538 0.66452 -0.2419 0.0019 1.0000 49.000 0.8032 0.66902 0.66819 -0.2439 0.0017 1.0000 49.500 0.7966 0.67208 0.67127 -0.2458 0.0016 1.0000 50.000 0.7897 0.67459 0.67381 -0.2477 0.0016 1.0000 50.500 0.7823 0.67660 0.67584 -0.2496 0.0015 1.0000 52.000 0.7604 0.68391 0.68321 -0.2546 0.0015 1.0000 52.500 0.7527 0.68509 0.68442 -0.2561 0.0015 1.0000 53.000 0.7451 0.68678 0.68614 -0.2576 0.0014 1.0000 53.500 0.7370 0.68731 0.68669 -0.2590 0.0014 1.0000 54.000 0.7287 0.68749 0.68689 -0.2604 0.0013 1.0000 54.500 0.7202 0.68743 0.68685 -0.2618 0.0013 1.0000 55.000 0.7115 0.68680 0.68625 -0.2631 0.0012 1.0000 55.500 0.7025 0.68555 0.68501 -0.2643 0.0011 1.0000 56.000 0.6934 0.68401 0.68349 -0.2655 0.0010 1.0000 56.500 0.6840 0.68199 0.68150 -0.2667 0.0010 1.0000 57.000 0.6746 0.67952 0.67905 -0.2678 0.0009 1.0000 57.500 0.6649 0.67678 0.67632 -0.2688 0.0009 1.0000 58.000 0.6551 0.67351 0.67307 -0.2699 0.0008 1.0000 58.500 0.6452 0.66987 0.66945 -0.2708 0.0008 1.0000 59.000 0.6350 0.66568 0.66528 -0.2717 0.0007 1.0000 59.500 0.6246 0.66107 0.66068 -0.2726 0.0007 1.0000 60.000 0.6141 0.65615 0.65578 -0.2734 0.0007 1.0000