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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.7125 0.04466 0.04251 -0.0549 1.0000 0.0060 -10.500 -0.7269 0.04309 0.04091 -0.0525 1.0000 0.0057 -10.250 -0.7744 0.03727 0.03474 -0.0473 1.0000 0.0058 -10.000 -0.7871 0.03257 0.02964 -0.0450 0.9994 0.0059 -9.750 -0.7740 0.02858 0.02526 -0.0462 0.9970 0.0059 -9.500 -0.7535 0.02596 0.02235 -0.0470 0.9950 0.0060 -9.250 -0.7310 0.02408 0.02023 -0.0474 0.9929 0.0060 -9.000 -0.7040 0.02261 0.01856 -0.0483 0.9911 0.0061 -8.750 -0.6755 0.02116 0.01691 -0.0493 0.9898 0.0062 -8.500 -0.6511 0.01986 0.01544 -0.0493 0.9870 0.0062 -8.250 -0.6245 0.01883 0.01427 -0.0495 0.9842 0.0062 -8.000 -0.5977 0.01793 0.01325 -0.0497 0.9812 0.0063 -7.750 -0.5709 0.01693 0.01212 -0.0498 0.9779 0.0063 -7.250 -0.5160 0.01545 0.01046 -0.0500 0.9695 0.0063 -7.000 -0.4957 0.01472 0.00964 -0.0485 0.9599 0.0063 -6.750 -0.4727 0.01395 0.00880 -0.0475 0.9478 0.0064 -6.500 -0.4380 0.01281 0.00754 -0.0491 0.9368 0.0065 -6.250 -0.3846 0.01190 0.00653 -0.0548 0.9218 0.0067 -6.000 -0.3394 0.01136 0.00582 -0.0586 0.8790 0.0069 -5.750 -0.3156 0.01114 0.00536 -0.0576 0.8267 0.0070 -5.500 -0.2943 0.01097 0.00499 -0.0560 0.7818 0.0070 -5.250 -0.2724 0.01077 0.00460 -0.0546 0.7448 0.0070 -5.000 -0.2491 0.01054 0.00425 -0.0535 0.7183 0.0071 -4.750 -0.2249 0.01030 0.00392 -0.0526 0.6979 0.0073 -4.500 -0.2005 0.01009 0.00361 -0.0518 0.6771 0.0074 -4.250 -0.1758 0.00990 0.00333 -0.0510 0.6570 0.0075 -4.000 -0.1507 0.00972 0.00307 -0.0502 0.6388 0.0077 -3.750 -0.1254 0.00957 0.00284 -0.0495 0.6206 0.0078 -3.500 -0.0999 0.00944 0.00262 -0.0488 0.6021 0.0080 -3.250 -0.0745 0.00935 0.00244 -0.0482 0.5806 0.0084 -3.000 -0.0487 0.00925 0.00226 -0.0476 0.5631 0.0086 -2.750 -0.0227 0.00913 0.00208 -0.0470 0.5488 0.0092 -2.500 0.0036 0.00904 0.00194 -0.0465 0.5361 0.0099 -2.250 0.0299 0.00898 0.00182 -0.0460 0.5221 0.0105 -2.000 0.0562 0.00893 0.00171 -0.0455 0.5069 0.0119 -1.500 0.1071 0.00862 0.00150 -0.0443 0.4745 0.0653 -1.250 0.1316 0.00833 0.00141 -0.0436 0.4622 0.1354 -1.000 0.1554 0.00797 0.00132 -0.0428 0.4510 0.2329 -0.750 0.1787 0.00757 0.00126 -0.0419 0.4401 0.3508 -0.500 0.2039 0.00742 0.00124 -0.0413 0.4294 0.4133 -0.250 0.2286 0.00726 0.00125 -0.0406 0.4178 0.4792 0.000 0.2541 0.00716 0.00125 -0.0400 0.4060 0.5267 0.250 0.2779 0.00701 0.00127 -0.0391 0.3928 0.5994 0.500 0.3012 0.00688 0.00133 -0.0380 0.3802 0.6762 0.750 0.3269 0.00690 0.00137 -0.0374 0.3675 0.7059 1.000 0.3533 0.00695 0.00140 -0.0369 0.3547 0.7222 1.250 0.3796 0.00702 0.00144 -0.0364 0.3411 0.7360 1.500 0.4058 0.00712 0.00149 -0.0359 0.3249 0.7482 1.750 0.4314 0.00722 0.00155 -0.0354 0.3056 0.7616 2.000 0.4562 0.00734 0.00163 -0.0346 0.2839 0.7790 2.250 0.4807 0.00741 0.00171 -0.0338 0.2675 0.8039 2.500 0.5050 0.00745 0.00180 -0.0329 0.2556 0.8387 2.750 0.5296 0.00746 0.00193 -0.0319 0.2454 0.9004 3.000 0.5636 0.00761 0.00208 -0.0332 0.2319 0.9304 3.250 0.6054 0.00776 0.00222 -0.0362 0.2256 0.9533 3.500 0.6469 0.00793 0.00235 -0.0392 0.2197 0.9653 3.750 0.6851 0.00808 0.00248 -0.0415 0.2143 0.9732 4.000 0.7203 0.00821 0.00259 -0.0430 0.2099 0.9802 4.250 0.7511 0.00837 0.00272 -0.0437 0.2041 0.9868 4.500 0.7821 0.00854 0.00285 -0.0443 0.1985 0.9922 4.750 0.8132 0.00867 0.00298 -0.0451 0.1928 0.9963 5.000 0.8459 0.00888 0.00312 -0.0462 0.1828 0.9992 5.250 0.8737 0.00905 0.00325 -0.0462 0.1743 1.0000 5.500 0.8967 0.00923 0.00340 -0.0452 0.1659 1.0000 5.750 0.9193 0.00946 0.00356 -0.0441 0.1547 1.0000 6.000 0.9408 0.00976 0.00377 -0.0429 0.1368 1.0000 6.250 0.9607 0.01019 0.00406 -0.0414 0.1136 1.0000 6.500 0.9807 0.01062 0.00438 -0.0399 0.0952 1.0000 6.750 1.0022 0.01095 0.00466 -0.0387 0.0856 1.0000 7.000 1.0241 0.01124 0.00492 -0.0376 0.0791 1.0000 7.250 1.0459 0.01154 0.00520 -0.0365 0.0738 1.0000 7.500 1.0683 0.01180 0.00545 -0.0354 0.0702 1.0000 7.750 1.0905 0.01207 0.00572 -0.0344 0.0666 1.0000 8.000 1.1121 0.01239 0.00602 -0.0332 0.0630 1.0000 8.250 1.1345 0.01264 0.00628 -0.0322 0.0607 1.0000 8.500 1.1563 0.01293 0.00657 -0.0311 0.0579 1.0000 8.750 1.1774 0.01327 0.00690 -0.0300 0.0548 1.0000 9.000 1.1993 0.01355 0.00720 -0.0289 0.0529 1.0000 9.250 1.2208 0.01385 0.00751 -0.0279 0.0507 1.0000 9.500 1.2414 0.01420 0.00786 -0.0267 0.0484 1.0000 9.750 1.2622 0.01454 0.00822 -0.0255 0.0466 1.0000 10.000 1.2830 0.01486 0.00856 -0.0244 0.0451 1.0000 10.250 1.3032 0.01522 0.00894 -0.0231 0.0435 1.0000 10.500 1.3223 0.01563 0.00935 -0.0218 0.0417 1.0000 10.750 1.3416 0.01601 0.00976 -0.0204 0.0402 1.0000 11.000 1.3605 0.01639 0.01016 -0.0190 0.0386 1.0000 11.250 1.3786 0.01680 0.01060 -0.0176 0.0376 1.0000 11.500 1.3951 0.01724 0.01106 -0.0158 0.0367 1.0000 11.750 1.4092 0.01771 0.01156 -0.0136 0.0357 1.0000 12.000 1.4233 0.01817 0.01205 -0.0115 0.0351 1.0000 12.250 1.4380 0.01861 0.01255 -0.0095 0.0345 1.0000 12.500 1.4522 0.01910 0.01308 -0.0076 0.0339 1.0000 12.750 1.4659 0.01962 0.01366 -0.0056 0.0332 1.0000 13.000 1.4786 0.02022 0.01429 -0.0037 0.0322 1.0000 13.250 1.4906 0.02088 0.01499 -0.0017 0.0318 1.0000 13.500 1.5014 0.02163 0.01578 0.0002 0.0311 1.0000 13.750 1.5110 0.02247 0.01668 0.0022 0.0305 1.0000 14.000 1.5218 0.02330 0.01757 0.0038 0.0301 1.0000 14.250 1.5324 0.02418 0.01852 0.0053 0.0296 1.0000 14.500 1.5420 0.02518 0.01960 0.0067 0.0291 1.0000 14.750 1.5505 0.02634 0.02083 0.0079 0.0287 1.0000 15.000 1.5581 0.02765 0.02220 0.0090 0.0282 1.0000 15.250 1.5644 0.02917 0.02379 0.0098 0.0275 1.0000 15.500 1.5697 0.03089 0.02558 0.0105 0.0271 1.0000 15.750 1.5731 0.03292 0.02768 0.0108 0.0266 1.0000 16.000 1.5751 0.03521 0.03006 0.0110 0.0261 1.0000 16.250 1.5773 0.03759 0.03253 0.0109 0.0258 1.0000 16.500 1.5794 0.04009 0.03513 0.0106 0.0256 1.0000 16.750 1.5815 0.04265 0.03778 0.0101 0.0249 1.0000 17.000 1.5797 0.04574 0.04097 0.0095 0.0245 1.0000 17.250 1.5758 0.04916 0.04449 0.0086 0.0242 1.0000 17.500 1.5702 0.05284 0.04825 0.0076 0.0235 1.0000 17.750 1.5614 0.05700 0.05252 0.0063 0.0232 1.0000 18.000 1.5504 0.06155 0.05716 0.0048 0.0227 1.0000 18.250 1.5369 0.06652 0.06224 0.0031 0.0225 1.0000 18.500 1.5210 0.07195 0.06778 0.0011 0.0223 1.0000 18.750 1.5101 0.07676 0.07269 -0.0007 0.0213 1.0000 19.000 1.4907 0.08289 0.07894 -0.0031 0.0219 1.0000 19.250 1.4760 0.08843 0.08459 -0.0053 0.0210 1.0000