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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4441 0.08560 0.08327 -0.0274 1.0000 0.0212 -9.000 -0.4490 0.08122 0.07892 -0.0293 1.0000 0.0217 -8.750 -0.4608 0.07541 0.07315 -0.0326 1.0000 0.0223 -8.500 -0.4761 0.06969 0.06747 -0.0365 1.0000 0.0221 -8.250 -0.5066 0.06380 0.06155 -0.0392 1.0000 0.0218 -8.000 -0.5234 0.05879 0.05645 -0.0393 1.0000 0.0221 -7.750 -0.5368 0.05387 0.05137 -0.0384 1.0000 0.0225 -7.500 -0.5696 0.04513 0.04205 -0.0355 1.0000 0.0237 -7.250 -0.5597 0.04378 0.04077 -0.0338 1.0000 0.0240 -7.000 -0.5542 0.04169 0.03859 -0.0317 1.0000 0.0242 -6.750 -0.5365 0.03944 0.03623 -0.0319 0.9986 0.0247 -6.500 -0.5108 0.03377 0.02988 -0.0346 0.9941 0.0280 -6.250 -0.4784 0.03183 0.02793 -0.0369 0.9910 0.0287 -6.000 -0.4488 0.02881 0.02435 -0.0384 0.9864 0.0327 -5.750 -0.4218 0.02083 0.01531 -0.0374 0.9828 0.0202 -5.500 -0.3889 0.01911 0.01348 -0.0382 0.9782 0.0189 -5.250 -0.3520 0.01758 0.01174 -0.0399 0.9754 0.0189 -5.000 -0.3209 0.01592 0.00993 -0.0403 0.9693 0.0179 -4.750 -0.2882 0.01458 0.00837 -0.0407 0.9629 0.0169 -4.500 -0.2556 0.01375 0.00748 -0.0413 0.9543 0.0167 -4.250 -0.2246 0.01296 0.00665 -0.0416 0.9430 0.0166 -4.000 -0.1920 0.01203 0.00572 -0.0424 0.9313 0.0168 -3.750 -0.1516 0.01122 0.00491 -0.0448 0.9202 0.0170 -3.500 -0.1066 0.01054 0.00422 -0.0483 0.9047 0.0177 -3.250 -0.0633 0.01006 0.00365 -0.0514 0.8793 0.0189 -3.000 -0.0292 0.00973 0.00317 -0.0524 0.8463 0.0205 -2.750 -0.0020 0.00959 0.00287 -0.0519 0.8115 0.0227 -2.500 0.0225 0.00944 0.00259 -0.0508 0.7802 0.0286 -2.250 0.0414 0.00861 0.00226 -0.0491 0.7530 0.1692 -2.000 0.0589 0.00777 0.00208 -0.0473 0.7291 0.3785 -1.750 0.0803 0.00748 0.00203 -0.0459 0.7074 0.4800 -1.500 0.1021 0.00727 0.00199 -0.0445 0.6859 0.5554 -1.250 0.1238 0.00711 0.00199 -0.0429 0.6649 0.6270 -1.000 0.1457 0.00702 0.00202 -0.0413 0.6450 0.6954 -0.750 0.1685 0.00697 0.00202 -0.0399 0.6261 0.7453 -0.500 0.1923 0.00692 0.00200 -0.0387 0.6090 0.7791 -0.250 0.2159 0.00684 0.00201 -0.0374 0.5932 0.8239 0.000 0.2429 0.00681 0.00210 -0.0366 0.5775 0.8905 0.250 0.2807 0.00689 0.00216 -0.0384 0.5611 0.9240 0.500 0.3194 0.00703 0.00221 -0.0404 0.5449 0.9459 0.750 0.3587 0.00717 0.00225 -0.0427 0.5284 0.9603 1.000 0.4009 0.00733 0.00230 -0.0456 0.5113 0.9687 1.250 0.4396 0.00748 0.00236 -0.0478 0.4956 0.9772 1.500 0.4776 0.00763 0.00241 -0.0499 0.4800 0.9854 1.750 0.5186 0.00777 0.00246 -0.0527 0.4636 0.9917 2.000 0.5590 0.00790 0.00249 -0.0554 0.4459 0.9972 2.250 0.5932 0.00802 0.00253 -0.0568 0.4283 1.0000 2.500 0.6147 0.00815 0.00257 -0.0555 0.4118 1.0000 2.750 0.6365 0.00829 0.00264 -0.0542 0.3947 1.0000 3.000 0.6581 0.00847 0.00271 -0.0529 0.3738 1.0000 3.250 0.6791 0.00870 0.00281 -0.0515 0.3492 1.0000 3.500 0.7006 0.00892 0.00292 -0.0502 0.3257 1.0000 3.750 0.7223 0.00916 0.00306 -0.0489 0.3059 1.0000 4.000 0.7442 0.00939 0.00320 -0.0477 0.2909 1.0000 4.250 0.7663 0.00963 0.00337 -0.0465 0.2792 1.0000 4.500 0.7884 0.00988 0.00354 -0.0453 0.2677 1.0000 4.750 0.8112 0.01008 0.00372 -0.0443 0.2593 1.0000 5.000 0.8336 0.01032 0.00392 -0.0431 0.2522 1.0000 5.250 0.8565 0.01053 0.00412 -0.0421 0.2460 1.0000 5.500 0.8794 0.01075 0.00432 -0.0411 0.2392 1.0000 5.750 0.9014 0.01104 0.00456 -0.0399 0.2322 1.0000 6.000 0.9251 0.01120 0.00475 -0.0391 0.2261 1.0000 6.250 0.9474 0.01146 0.00499 -0.0380 0.2193 1.0000 6.500 0.9705 0.01167 0.00522 -0.0370 0.2135 1.0000 6.750 0.9941 0.01185 0.00542 -0.0362 0.2070 1.0000 7.000 1.0162 0.01213 0.00567 -0.0351 0.1992 1.0000 7.250 1.0404 0.01227 0.00585 -0.0344 0.1904 1.0000 7.500 1.0632 0.01251 0.00607 -0.0334 0.1793 1.0000 7.750 1.0852 0.01280 0.00631 -0.0324 0.1615 1.0000 8.000 1.1046 0.01330 0.00665 -0.0310 0.1344 1.0000 8.250 1.1215 0.01399 0.00716 -0.0293 0.1098 1.0000 8.500 1.1391 0.01462 0.00772 -0.0276 0.0970 1.0000 8.750 1.1576 0.01517 0.00825 -0.0260 0.0894 1.0000 9.000 1.1742 0.01583 0.00887 -0.0242 0.0830 1.0000 9.250 1.1937 0.01627 0.00937 -0.0229 0.0791 1.0000 9.500 1.2107 0.01686 0.00996 -0.0211 0.0751 1.0000 9.750 1.2260 0.01754 0.01065 -0.0192 0.0713 1.0000 10.000 1.2439 0.01801 0.01119 -0.0176 0.0688 1.0000 10.250 1.2600 0.01858 0.01179 -0.0158 0.0661 1.0000 10.500 1.2700 0.01938 0.01260 -0.0131 0.0637 1.0000 10.750 1.2805 0.02007 0.01335 -0.0104 0.0620 1.0000 11.000 1.2938 0.02063 0.01398 -0.0082 0.0605 1.0000 11.250 1.3059 0.02127 0.01469 -0.0060 0.0591 1.0000 11.500 1.3170 0.02198 0.01545 -0.0037 0.0578 1.0000 11.750 1.3254 0.02286 0.01637 -0.0013 0.0564 1.0000 12.000 1.3295 0.02405 0.01759 0.0015 0.0552 1.0000 12.250 1.3359 0.02517 0.01878 0.0037 0.0541 1.0000 12.500 1.3458 0.02612 0.01983 0.0054 0.0533 1.0000 12.750 1.3562 0.02707 0.02087 0.0068 0.0523 1.0000 13.000 1.3646 0.02823 0.02210 0.0082 0.0512 1.0000 13.250 1.3720 0.02953 0.02348 0.0094 0.0504 1.0000 13.500 1.3783 0.03101 0.02502 0.0105 0.0495 1.0000 13.750 1.3825 0.03276 0.02683 0.0113 0.0487 1.0000 14.000 1.3829 0.03498 0.02910 0.0121 0.0479 1.0000 14.250 1.3816 0.03745 0.03164 0.0129 0.0472 1.0000 14.500 1.3874 0.03938 0.03369 0.0130 0.0468 1.0000 14.750 1.3923 0.04148 0.03590 0.0130 0.0462 1.0000 15.000 1.3967 0.04370 0.03824 0.0128 0.0454 1.0000 15.250 1.3994 0.04617 0.04081 0.0124 0.0446 1.0000 15.500 1.4011 0.04879 0.04351 0.0119 0.0440 1.0000 15.750 1.4012 0.05159 0.04641 0.0115 0.0436 1.0000 16.000 1.4014 0.05454 0.04943 0.0107 0.0429 1.0000 16.250 1.3999 0.05766 0.05262 0.0099 0.0424 1.0000 16.500 1.3979 0.06085 0.05588 0.0091 0.0419 1.0000 16.750 1.3943 0.06408 0.05914 0.0086 0.0412 1.0000 17.000 1.3917 0.06747 0.06263 0.0077 0.0407 1.0000 17.250 1.3886 0.07121 0.06651 0.0063 0.0404 1.0000 17.500 1.3843 0.07517 0.07060 0.0047 0.0399 1.0000 17.750 1.3795 0.07928 0.07483 0.0029 0.0394 1.0000 18.000 1.3744 0.08350 0.07918 0.0011 0.0388 1.0000 18.250 1.3694 0.08779 0.08356 -0.0009 0.0383 1.0000