XFOIL Version 6.96 Calculated polar for: DEFIANT CANARD BL145 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4215 0.10493 0.10115 -0.0218 1.0000 0.0480 -9.750 -0.4271 0.10052 0.09678 -0.0250 1.0000 0.0495 -9.500 -0.4522 0.09326 0.08961 -0.0341 1.0000 0.0503 -9.250 -0.4453 0.09007 0.08646 -0.0318 1.0000 0.0510 -9.000 -0.4328 0.08858 0.08498 -0.0289 1.0000 0.0520 -8.750 -0.4286 0.08608 0.08251 -0.0285 1.0000 0.0538 -8.500 -0.4331 0.08228 0.07877 -0.0301 1.0000 0.0548 -8.250 -0.4472 0.07742 0.07398 -0.0334 1.0000 0.0564 -8.000 -0.4683 0.07258 0.06919 -0.0362 1.0000 0.0565 -7.750 -0.4875 0.06742 0.06394 -0.0383 1.0000 0.0572 -7.500 -0.5347 0.06346 0.05930 -0.0380 1.0000 0.0585 -7.250 -0.5087 0.05901 0.05534 -0.0373 1.0000 0.0602 -7.000 -0.5033 0.05660 0.05293 -0.0358 1.0000 0.0611 -6.750 -0.4985 0.05428 0.05058 -0.0343 1.0000 0.0631 -6.000 -0.4900 0.04590 0.04182 -0.0290 1.0000 0.0726 -5.750 -0.4918 0.04389 0.03921 -0.0261 1.0000 0.0801 -5.500 -0.4809 0.04105 0.03652 -0.0246 1.0000 0.0816 -5.250 -0.4692 0.03916 0.03466 -0.0230 0.9997 0.0839 -5.000 -0.4341 0.02678 0.02010 -0.0218 0.9948 0.0379 -4.750 -0.3941 0.02412 0.01724 -0.0241 0.9900 0.0349 -4.500 -0.3530 0.02175 0.01422 -0.0257 0.9841 0.0318 -4.250 -0.3128 0.02004 0.01239 -0.0279 0.9779 0.0314 -4.000 -0.2723 0.01866 0.01089 -0.0300 0.9709 0.0315 -3.750 -0.2325 0.01749 0.00966 -0.0320 0.9629 0.0319 -3.500 -0.1948 0.01625 0.00851 -0.0338 0.9539 0.0330 -3.250 -0.1547 0.01530 0.00761 -0.0360 0.9454 0.0353 -3.000 -0.1166 0.01442 0.00678 -0.0378 0.9347 0.0403 -2.750 -0.0794 0.01358 0.00594 -0.0392 0.9224 0.0473 -2.500 -0.0472 0.01149 0.00486 -0.0402 0.9084 0.2464 -2.250 -0.0161 0.01017 0.00460 -0.0409 0.8924 0.5180 -2.000 0.0159 0.00951 0.00456 -0.0408 0.8741 0.6812 -1.750 0.0510 0.00923 0.00441 -0.0411 0.8529 0.7607 -1.500 0.0834 0.00907 0.00428 -0.0411 0.8281 0.8049 -1.250 0.1162 0.00905 0.00421 -0.0410 0.8031 0.8499 -1.000 0.1541 0.00919 0.00425 -0.0418 0.7788 0.8992 -0.750 0.2002 0.00943 0.00432 -0.0444 0.7518 0.9323 -0.500 0.2446 0.00962 0.00428 -0.0473 0.7269 0.9485 -0.250 0.2897 0.00980 0.00425 -0.0505 0.7048 0.9616 0.000 0.3351 0.00995 0.00422 -0.0539 0.6821 0.9736 0.250 0.3813 0.01007 0.00415 -0.0576 0.6599 0.9850 0.500 0.4289 0.01015 0.00405 -0.0618 0.6380 0.9956 0.750 0.4600 0.01019 0.00394 -0.0627 0.6193 1.0000 1.000 0.4784 0.01024 0.00388 -0.0611 0.6028 1.0000 1.250 0.4979 0.01033 0.00386 -0.0595 0.5868 1.0000 1.500 0.5181 0.01045 0.00387 -0.0580 0.5708 1.0000 1.750 0.5388 0.01059 0.00389 -0.0565 0.5546 1.0000 2.000 0.5599 0.01074 0.00394 -0.0551 0.5385 1.0000 2.250 0.5812 0.01091 0.00400 -0.0537 0.5220 1.0000 2.500 0.6027 0.01109 0.00408 -0.0524 0.5056 1.0000 2.750 0.6242 0.01127 0.00418 -0.0510 0.4884 1.0000 3.000 0.6456 0.01148 0.00429 -0.0496 0.4703 1.0000 3.250 0.6669 0.01168 0.00442 -0.0482 0.4505 1.0000 3.500 0.6882 0.01192 0.00457 -0.0468 0.4302 1.0000 3.750 0.7095 0.01219 0.00476 -0.0454 0.4103 1.0000 4.000 0.7309 0.01248 0.00496 -0.0441 0.3916 1.0000 4.250 0.7522 0.01279 0.00517 -0.0427 0.3739 1.0000 4.500 0.7737 0.01309 0.00538 -0.0414 0.3576 1.0000 4.750 0.7953 0.01341 0.00562 -0.0402 0.3432 1.0000 5.000 0.8169 0.01374 0.00585 -0.0390 0.3306 1.0000 5.250 0.8391 0.01401 0.00610 -0.0378 0.3182 1.0000 5.500 0.8616 0.01432 0.00639 -0.0368 0.3081 1.0000 5.750 0.8838 0.01469 0.00670 -0.0357 0.2992 1.0000 6.000 0.9066 0.01497 0.00703 -0.0347 0.2901 1.0000 6.500 0.9512 0.01565 0.00770 -0.0327 0.2726 1.0000 6.750 0.9728 0.01605 0.00805 -0.0316 0.2638 1.0000 7.000 0.9945 0.01635 0.00839 -0.0305 0.2539 1.0000 7.250 1.0158 0.01673 0.00880 -0.0293 0.2443 1.0000 7.500 1.0362 0.01716 0.00917 -0.0281 0.2341 1.0000 7.750 1.0570 0.01744 0.00957 -0.0269 0.2227 1.0000 8.000 1.0767 0.01783 0.00999 -0.0255 0.2103 1.0000 8.250 1.0958 0.01815 0.01036 -0.0241 0.1951 1.0000 8.500 1.1144 0.01847 0.01070 -0.0226 0.1746 1.0000 8.750 1.1308 0.01903 0.01118 -0.0208 0.1521 1.0000 9.000 1.1452 0.01980 0.01184 -0.0187 0.1342 1.0000 9.250 1.1588 0.02066 0.01264 -0.0166 0.1225 1.0000 9.500 1.1710 0.02160 0.01352 -0.0144 0.1141 1.0000 9.750 1.1830 0.02252 0.01443 -0.0121 0.1075 1.0000 10.000 1.1937 0.02352 0.01543 -0.0097 0.1027 1.0000 10.250 1.2049 0.02440 0.01636 -0.0073 0.0984 1.0000 10.500 1.2136 0.02554 0.01744 -0.0048 0.0949 1.0000 10.750 1.2250 0.02668 0.01864 -0.0027 0.0918 1.0000 11.000 1.2370 0.02767 0.01973 -0.0007 0.0889 1.0000 11.250 1.2488 0.02874 0.02083 0.0011 0.0863 1.0000 11.500 1.2618 0.03002 0.02208 0.0026 0.0839 1.0000 11.750 1.2778 0.03152 0.02361 0.0037 0.0817 1.0000 12.000 1.2892 0.03269 0.02493 0.0054 0.0801 1.0000 12.250 1.3006 0.03396 0.02634 0.0070 0.0785 1.0000 12.500 1.3125 0.03531 0.02780 0.0084 0.0771 1.0000 12.750 1.3249 0.03669 0.02926 0.0096 0.0757 1.0000 13.000 1.3394 0.03817 0.03078 0.0105 0.0743 1.0000 13.250 1.3613 0.04025 0.03286 0.0106 0.0726 1.0000 13.500 1.3673 0.04224 0.03505 0.0121 0.0717 1.0000 13.750 1.3680 0.04400 0.03703 0.0139 0.0710 1.0000 14.000 1.3671 0.04601 0.03926 0.0155 0.0701 1.0000 14.250 1.3657 0.04826 0.04172 0.0167 0.0693 1.0000 14.500 1.3625 0.05056 0.04420 0.0177 0.0682 1.0000 14.750 1.3606 0.05294 0.04671 0.0183 0.0671 1.0000 15.000 1.3584 0.05531 0.04920 0.0186 0.0659 1.0000 15.250 1.3647 0.05725 0.05114 0.0188 0.0644 1.0000 15.500 1.3725 0.06024 0.05416 0.0190 0.0627 1.0000 15.750 1.3542 0.06408 0.05825 0.0184 0.0623 1.0000 16.000 1.3363 0.06854 0.06295 0.0171 0.0619 1.0000 16.250 1.3161 0.07370 0.06835 0.0152 0.0616 1.0000 16.500 1.2929 0.07963 0.07452 0.0125 0.0614 1.0000 16.750 1.2638 0.08686 0.08198 0.0087 0.0612 1.0000 17.000 1.2300 0.09553 0.09089 0.0037 0.0613 1.0000 17.250 1.1859 0.10684 0.10244 -0.0032 0.0617 1.0000 17.500 1.1251 0.12278 0.11862 -0.0132 0.0625 1.0000