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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.4758 0.09380 0.09129 -0.0240 1.0000 0.0085 -10.250 -0.4843 0.08805 0.08557 -0.0264 1.0000 0.0085 -10.000 -0.5050 0.07944 0.07700 -0.0304 1.0000 0.0085 -9.750 -0.5052 0.07642 0.07400 -0.0319 1.0000 0.0083 -9.500 -0.5264 0.06792 0.06555 -0.0373 1.0000 0.0082 -9.250 -0.5832 0.05458 0.05208 -0.0466 1.0000 0.0081 -9.000 -0.6316 0.04576 0.04296 -0.0442 1.0000 0.0081 -8.750 -0.6660 0.03810 0.03482 -0.0405 1.0000 0.0081 -8.500 -0.6746 0.03371 0.03005 -0.0373 0.9999 0.0081 -8.250 -0.6569 0.02892 0.02468 -0.0388 0.9965 0.0082 -8.000 -0.6331 0.02598 0.02134 -0.0398 0.9934 0.0082 -7.750 -0.6057 0.02370 0.01872 -0.0409 0.9905 0.0083 -7.500 -0.5778 0.02195 0.01669 -0.0417 0.9874 0.0083 -7.250 -0.5479 0.02097 0.01543 -0.0424 0.9837 0.0086 -7.000 -0.5207 0.01959 0.01386 -0.0427 0.9793 0.0086 -6.500 -0.4643 0.01709 0.01111 -0.0434 0.9695 0.0089 -6.250 -0.4395 0.01622 0.01015 -0.0428 0.9608 0.0090 -6.000 -0.4160 0.01541 0.00926 -0.0419 0.9495 0.0091 -5.750 -0.3883 0.01464 0.00842 -0.0418 0.9387 0.0091 -5.500 -0.3548 0.01389 0.00761 -0.0430 0.9283 0.0092 -5.250 -0.3123 0.01311 0.00676 -0.0460 0.9178 0.0093 -5.000 -0.2640 0.01237 0.00596 -0.0504 0.9019 0.0095 -4.750 -0.2175 0.01177 0.00521 -0.0543 0.8685 0.0098 -4.500 -0.1872 0.01145 0.00469 -0.0546 0.8247 0.0100 -4.250 -0.1630 0.01126 0.00431 -0.0536 0.7856 0.0102 -4.000 -0.1394 0.01107 0.00396 -0.0525 0.7557 0.0106 -3.750 -0.1153 0.01089 0.00365 -0.0515 0.7314 0.0108 -3.500 -0.0912 0.01072 0.00336 -0.0505 0.7087 0.0112 -3.000 -0.0421 0.01043 0.00286 -0.0488 0.6670 0.0127 -2.750 -0.0171 0.01034 0.00266 -0.0480 0.6454 0.0136 -2.500 0.0077 0.01023 0.00248 -0.0472 0.6246 0.0158 -2.250 0.0325 0.01007 0.00229 -0.0464 0.6055 0.0257 -2.000 0.0563 0.00976 0.00212 -0.0455 0.5890 0.0767 -1.750 0.0801 0.00944 0.00199 -0.0447 0.5747 0.1430 -1.500 0.1017 0.00889 0.00184 -0.0436 0.5589 0.2721 -1.250 0.1235 0.00846 0.00178 -0.0425 0.5427 0.4057 -1.000 0.1469 0.00823 0.00175 -0.0415 0.5265 0.4837 -0.750 0.1701 0.00803 0.00174 -0.0405 0.5111 0.5544 -0.500 0.1941 0.00792 0.00174 -0.0395 0.4978 0.6076 -0.250 0.2175 0.00782 0.00178 -0.0383 0.4858 0.6687 0.000 0.2412 0.00774 0.00181 -0.0372 0.4734 0.7245 0.250 0.2666 0.00773 0.00181 -0.0365 0.4617 0.7503 0.500 0.2924 0.00775 0.00182 -0.0358 0.4497 0.7678 0.750 0.3179 0.00776 0.00185 -0.0351 0.4369 0.7876 1.000 0.3434 0.00776 0.00188 -0.0344 0.4234 0.8159 1.250 0.3694 0.00778 0.00194 -0.0337 0.4096 0.8500 1.500 0.3994 0.00783 0.00203 -0.0339 0.3958 0.8960 1.750 0.4375 0.00796 0.00213 -0.0360 0.3804 0.9225 2.000 0.4784 0.00813 0.00222 -0.0387 0.3634 0.9445 2.250 0.5161 0.00831 0.00232 -0.0408 0.3454 0.9590 2.500 0.5545 0.00852 0.00242 -0.0430 0.3238 0.9684 2.750 0.5890 0.00874 0.00253 -0.0445 0.3038 0.9770 3.000 0.6211 0.00896 0.00266 -0.0454 0.2865 0.9858 3.750 0.7149 0.00968 0.00310 -0.0479 0.2418 1.0000 4.000 0.7373 0.00988 0.00325 -0.0467 0.2350 1.0000 4.250 0.7604 0.01005 0.00340 -0.0457 0.2301 1.0000 4.500 0.7834 0.01023 0.00355 -0.0447 0.2236 1.0000 4.750 0.8058 0.01046 0.00374 -0.0436 0.2171 1.0000 5.000 0.8294 0.01061 0.00390 -0.0426 0.2130 1.0000 5.250 0.8529 0.01077 0.00406 -0.0417 0.2078 1.0000 5.500 0.8757 0.01100 0.00426 -0.0407 0.2011 1.0000 5.750 0.8992 0.01117 0.00444 -0.0398 0.1946 1.0000 6.000 0.9222 0.01139 0.00462 -0.0388 0.1861 1.0000 6.250 0.9453 0.01159 0.00482 -0.0379 0.1772 1.0000 6.500 0.9679 0.01184 0.00503 -0.0369 0.1671 1.0000 6.750 0.9901 0.01212 0.00526 -0.0358 0.1541 1.0000 7.000 1.0111 0.01250 0.00554 -0.0346 0.1349 1.0000 7.250 1.0304 0.01301 0.00592 -0.0331 0.1122 1.0000 7.500 1.0498 0.01351 0.00633 -0.0317 0.0967 1.0000 7.750 1.0699 0.01396 0.00673 -0.0304 0.0870 1.0000 8.000 1.0904 0.01438 0.00713 -0.0291 0.0808 1.0000 8.250 1.1111 0.01477 0.00752 -0.0279 0.0758 1.0000 8.500 1.1313 0.01519 0.00795 -0.0267 0.0717 1.0000 8.750 1.1522 0.01555 0.00834 -0.0255 0.0685 1.0000 9.000 1.1721 0.01598 0.00878 -0.0242 0.0653 1.0000 9.250 1.1913 0.01644 0.00925 -0.0229 0.0624 1.0000 9.500 1.2114 0.01682 0.00968 -0.0216 0.0602 1.0000 9.750 1.2303 0.01726 0.01015 -0.0202 0.0576 1.0000 10.000 1.2481 0.01777 0.01067 -0.0187 0.0555 1.0000 10.250 1.2658 0.01825 0.01119 -0.0172 0.0536 1.0000 10.500 1.2835 0.01870 0.01169 -0.0156 0.0519 1.0000 10.750 1.2989 0.01919 0.01223 -0.0137 0.0502 1.0000 11.000 1.3123 0.01974 0.01281 -0.0115 0.0487 1.0000 11.250 1.3239 0.02037 0.01348 -0.0091 0.0475 1.0000 11.500 1.3369 0.02095 0.01412 -0.0070 0.0466 1.0000 11.750 1.3498 0.02155 0.01479 -0.0050 0.0455 1.0000 12.000 1.3622 0.02220 0.01550 -0.0030 0.0444 1.0000 12.250 1.3737 0.02291 0.01626 -0.0010 0.0431 1.0000 12.500 1.3832 0.02377 0.01718 0.0010 0.0422 1.0000 12.750 1.3909 0.02477 0.01822 0.0030 0.0412 1.0000 13.000 1.3995 0.02578 0.01931 0.0048 0.0405 1.0000 13.250 1.4078 0.02687 0.02049 0.0063 0.0399 1.0000 13.500 1.4155 0.02808 0.02179 0.0077 0.0392 1.0000 13.750 1.4223 0.02944 0.02324 0.0089 0.0385 1.0000 14.000 1.4281 0.03100 0.02488 0.0098 0.0377 1.0000 14.250 1.4325 0.03278 0.02674 0.0105 0.0371 1.0000 14.500 1.4354 0.03484 0.02889 0.0110 0.0365 1.0000 14.750 1.4364 0.03722 0.03135 0.0111 0.0360 1.0000 15.000 1.4355 0.03996 0.03416 0.0110 0.0352 1.0000 15.250 1.4374 0.04251 0.03683 0.0107 0.0348 1.0000 15.500 1.4378 0.04528 0.03972 0.0102 0.0343 1.0000 15.750 1.4355 0.04848 0.04304 0.0095 0.0340 1.0000 16.000 1.4336 0.05173 0.04640 0.0086 0.0334 1.0000 16.250 1.4291 0.05534 0.05011 0.0076 0.0330 1.0000 16.500 1.4235 0.05917 0.05405 0.0064 0.0326 1.0000 16.750 1.4156 0.06340 0.05839 0.0050 0.0322 1.0000 17.000 1.4073 0.06776 0.06286 0.0034 0.0319 1.0000 17.250 1.3977 0.07243 0.06763 0.0016 0.0316 1.0000 17.500 1.3869 0.07738 0.07268 -0.0003 0.0312 1.0000 17.750 1.3756 0.08250 0.07789 -0.0024 0.0309 1.0000 18.000 1.3637 0.08781 0.08329 -0.0047 0.0306 1.0000