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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3350 0.09169 0.08666 -0.0294 1.0000 0.0310 -9.750 -0.3372 0.08752 0.08253 -0.0302 1.0000 0.0301 -9.250 -0.4548 0.08378 0.07853 -0.0337 1.0000 0.0273 -9.000 -0.4571 0.07996 0.07476 -0.0351 1.0000 0.0269 -8.750 -0.4655 0.07473 0.06958 -0.0380 1.0000 0.0265 -8.500 -0.4821 0.06922 0.06411 -0.0415 1.0000 0.0261 -8.250 -0.5008 0.06471 0.05956 -0.0418 1.0000 0.0257 -8.000 -0.5153 0.06010 0.05485 -0.0417 1.0000 0.0252 -7.750 -0.5285 0.05518 0.04973 -0.0408 1.0000 0.0245 -7.500 -0.5491 0.04797 0.04186 -0.0388 1.0000 0.0233 -7.250 -0.5458 0.04494 0.03860 -0.0369 1.0000 0.0232 -7.000 -0.5397 0.04216 0.03558 -0.0350 1.0000 0.0230 -6.750 -0.5321 0.03937 0.03251 -0.0330 1.0000 0.0229 -6.500 -0.5226 0.03671 0.02950 -0.0309 1.0000 0.0228 -6.250 -0.5110 0.03423 0.02669 -0.0289 1.0000 0.0228 -6.000 -0.4976 0.03193 0.02403 -0.0269 1.0000 0.0228 -5.750 -0.4823 0.02999 0.02177 -0.0250 1.0000 0.0229 -5.500 -0.4657 0.02830 0.01980 -0.0232 1.0000 0.0229 -5.250 -0.4481 0.02672 0.01794 -0.0214 1.0000 0.0231 -5.000 -0.4126 0.02507 0.01605 -0.0231 0.9944 0.0235 -4.750 -0.3748 0.02390 0.01484 -0.0255 0.9872 0.0250 -4.500 -0.3379 0.02272 0.01346 -0.0273 0.9788 0.0270 -4.250 -0.3022 0.02159 0.01232 -0.0289 0.9695 0.0285 -4.000 -0.2679 0.02056 0.01125 -0.0302 0.9585 0.0300 -3.750 -0.2342 0.01962 0.01022 -0.0312 0.9467 0.0316 -3.500 -0.2010 0.01874 0.00935 -0.0322 0.9340 0.0339 -3.250 -0.1678 0.01797 0.00850 -0.0330 0.9207 0.0379 -3.000 -0.1342 0.01720 0.00778 -0.0340 0.9069 0.0489 -2.750 -0.1003 0.01617 0.00703 -0.0351 0.8925 0.0957 -2.500 -0.0727 0.01436 0.00654 -0.0359 0.8773 0.3526 -2.250 -0.0450 0.01338 0.00653 -0.0353 0.8616 0.5837 -2.000 -0.0102 0.01307 0.00637 -0.0357 0.8447 0.6645 -1.750 0.0249 0.01287 0.00615 -0.0362 0.8259 0.7262 -1.500 0.0608 0.01267 0.00603 -0.0365 0.8056 0.7923 -1.250 0.1049 0.01263 0.00596 -0.0382 0.7836 0.8537 -1.000 0.1492 0.01267 0.00580 -0.0407 0.7593 0.8845 -0.750 0.1896 0.01274 0.00564 -0.0427 0.7331 0.9093 -0.500 0.2328 0.01282 0.00548 -0.0453 0.7080 0.9291 -0.250 0.2738 0.01292 0.00535 -0.0476 0.6831 0.9483 0.000 0.3158 0.01302 0.00524 -0.0503 0.6591 0.9648 0.250 0.3570 0.01311 0.00514 -0.0529 0.6380 0.9806 0.500 0.3988 0.01321 0.00504 -0.0558 0.6176 0.9960 0.750 0.4256 0.01331 0.00499 -0.0558 0.5996 1.0000 1.000 0.4465 0.01343 0.00498 -0.0545 0.5832 1.0000 1.250 0.4679 0.01357 0.00500 -0.0532 0.5673 1.0000 1.500 0.4894 0.01373 0.00504 -0.0519 0.5512 1.0000 1.750 0.5112 0.01390 0.00509 -0.0507 0.5353 1.0000 2.000 0.5330 0.01409 0.00517 -0.0494 0.5191 1.0000 2.250 0.5550 0.01429 0.00526 -0.0481 0.5035 1.0000 2.500 0.5771 0.01451 0.00538 -0.0469 0.4881 1.0000 2.750 0.5991 0.01472 0.00553 -0.0457 0.4723 1.0000 3.000 0.6211 0.01496 0.00569 -0.0445 0.4561 1.0000 3.250 0.6431 0.01520 0.00586 -0.0432 0.4397 1.0000 3.500 0.6650 0.01547 0.00606 -0.0420 0.4234 1.0000 3.750 0.6870 0.01575 0.00627 -0.0408 0.4079 1.0000 4.000 0.7090 0.01605 0.00652 -0.0396 0.3928 1.0000 4.250 0.7310 0.01637 0.00678 -0.0384 0.3783 1.0000 4.500 0.7529 0.01672 0.00704 -0.0373 0.3646 1.0000 4.750 0.7752 0.01706 0.00738 -0.0362 0.3517 1.0000 5.000 0.7977 0.01742 0.00773 -0.0351 0.3402 1.0000 5.250 0.8196 0.01781 0.00805 -0.0340 0.3290 1.0000 5.500 0.8413 0.01819 0.00839 -0.0329 0.3165 1.0000 5.750 0.8627 0.01856 0.00876 -0.0318 0.3029 1.0000 6.000 0.8836 0.01894 0.00911 -0.0306 0.2891 1.0000 6.250 0.9046 0.01935 0.00949 -0.0294 0.2774 1.0000 6.500 0.9257 0.01979 0.00992 -0.0283 0.2675 1.0000 6.750 0.9471 0.02022 0.01040 -0.0272 0.2578 1.0000 7.000 0.9675 0.02072 0.01085 -0.0260 0.2490 1.0000 7.250 0.9884 0.02117 0.01140 -0.0249 0.2389 1.0000 7.500 1.0082 0.02169 0.01193 -0.0237 0.2293 1.0000 7.750 1.0276 0.02220 0.01249 -0.0224 0.2187 1.0000 8.000 1.0470 0.02270 0.01310 -0.0211 0.2071 1.0000 8.250 1.0653 0.02323 0.01369 -0.0197 0.1948 1.0000 8.500 1.0831 0.02376 0.01429 -0.0182 0.1809 1.0000 8.750 1.1002 0.02433 0.01492 -0.0167 0.1652 1.0000 9.000 1.1157 0.02501 0.01562 -0.0150 0.1494 1.0000 9.250 1.1294 0.02581 0.01639 -0.0132 0.1357 1.0000 9.500 1.1414 0.02673 0.01728 -0.0112 0.1245 1.0000 9.750 1.1514 0.02776 0.01827 -0.0090 0.1163 1.0000 10.000 1.1609 0.02877 0.01933 -0.0067 0.1095 1.0000 10.250 1.1665 0.02992 0.02045 -0.0040 0.1046 1.0000 10.500 1.1745 0.03104 0.02167 -0.0017 0.0999 1.0000 10.750 1.1800 0.03231 0.02298 0.0007 0.0961 1.0000 11.000 1.1836 0.03375 0.02442 0.0030 0.0933 1.0000 11.250 1.1907 0.03511 0.02593 0.0048 0.0904 1.0000 11.500 1.1962 0.03660 0.02753 0.0065 0.0876 1.0000 11.750 1.2003 0.03826 0.02925 0.0080 0.0851 1.0000 12.000 1.2038 0.04006 0.03106 0.0093 0.0832 1.0000 12.250 1.2087 0.04189 0.03301 0.0104 0.0812 1.0000 12.500 1.2134 0.04383 0.03512 0.0112 0.0792 1.0000 12.750 1.2177 0.04585 0.03727 0.0119 0.0775 1.0000 13.000 1.2219 0.04798 0.03950 0.0125 0.0759 1.0000 13.250 1.2264 0.05012 0.04173 0.0130 0.0746 1.0000 13.500 1.2322 0.05221 0.04387 0.0134 0.0732 1.0000 13.750 1.2396 0.05428 0.04596 0.0138 0.0720 1.0000 14.000 1.2376 0.05730 0.04922 0.0137 0.0708 1.0000 14.250 1.2345 0.06053 0.05268 0.0132 0.0697 1.0000 14.500 1.2304 0.06400 0.05635 0.0125 0.0686 1.0000 14.750 1.2257 0.06765 0.06018 0.0116 0.0676 1.0000 15.000 1.2201 0.07151 0.06422 0.0105 0.0667 1.0000 15.250 1.2138 0.07558 0.06845 0.0091 0.0659 1.0000 15.500 1.2066 0.07989 0.07291 0.0075 0.0652 1.0000 15.750 1.1999 0.08425 0.07742 0.0058 0.0645 1.0000 16.000 1.1933 0.08869 0.08198 0.0041 0.0639 1.0000 16.250 1.1926 0.09228 0.08563 0.0029 0.0631 1.0000 16.500 1.1761 0.09864 0.09215 -0.0003 0.0627 1.0000 16.750 1.1370 0.10952 0.10331 -0.0071 0.0626 1.0000 17.000 1.0693 0.12777 0.12184 -0.0189 0.0627 1.0000