XFOIL Version 6.96 Calculated polar for: BOEING BACXXX 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.4973 0.10341 0.09977 -0.0406 1.0000 0.0364 -10.250 -0.5067 0.09821 0.09457 -0.0446 1.0000 0.0365 -8.500 -0.6184 0.07216 0.06845 -0.0380 1.0000 0.0378 -8.250 -0.6181 0.06901 0.06536 -0.0362 1.0000 0.0386 -8.000 -0.6235 0.06636 0.06269 -0.0337 1.0000 0.0393 -7.750 -0.6290 0.06372 0.05998 -0.0312 1.0000 0.0400 -7.500 -0.6331 0.06106 0.05723 -0.0287 1.0000 0.0408 -7.250 -0.6354 0.05838 0.05443 -0.0262 1.0000 0.0420 -7.000 -0.6355 0.05570 0.05160 -0.0237 1.0000 0.0435 -6.750 -0.6327 0.05333 0.04899 -0.0211 1.0000 0.0458 -6.500 -0.6270 0.05547 0.05047 -0.0166 1.0000 0.0486 -6.250 -0.6275 0.04799 0.04286 -0.0154 1.0000 0.0501 -6.000 -0.6160 0.04438 0.03931 -0.0144 1.0000 0.0516 -5.750 -0.6034 0.04191 0.03677 -0.0130 1.0000 0.0537 -5.500 -0.5894 0.03991 0.03457 -0.0114 1.0000 0.0574 -3.750 -0.4337 0.02394 0.01619 -0.0012 1.0000 0.0381 -3.500 -0.4086 0.02258 0.01468 -0.0005 1.0000 0.0380 -3.250 -0.3850 0.02245 0.01442 0.0007 1.0000 0.0367 -3.000 -0.3582 0.02027 0.01220 0.0011 1.0000 0.0353 -2.750 -0.3283 0.01907 0.01096 0.0008 0.9990 0.0348 -2.500 -0.2842 0.01808 0.00995 -0.0024 0.9951 0.0353 -2.250 -0.2405 0.01723 0.00906 -0.0057 0.9894 0.0369 -2.000 -0.1956 0.01630 0.00810 -0.0095 0.9839 0.0444 -1.750 -0.1604 0.01323 0.00737 -0.0121 0.9805 0.6201 -1.500 -0.1235 0.01318 0.00768 -0.0132 0.9743 0.7284 -1.250 -0.0878 0.01321 0.00783 -0.0141 0.9670 0.7771 -1.000 -0.0554 0.01318 0.00787 -0.0144 0.9590 0.8097 -0.750 -0.0147 0.01312 0.00779 -0.0169 0.9534 0.8277 -0.500 0.0160 0.01301 0.00768 -0.0173 0.9453 0.8447 -0.250 0.0552 0.01290 0.00757 -0.0193 0.9397 0.8628 0.000 0.0848 0.01277 0.00749 -0.0193 0.9313 0.8823 0.250 0.1247 0.01260 0.00733 -0.0212 0.9255 0.9024 0.500 0.1604 0.01246 0.00720 -0.0223 0.9172 0.9238 0.750 0.2107 0.01219 0.00693 -0.0264 0.9114 0.9393 1.000 0.2590 0.01190 0.00665 -0.0301 0.9033 0.9533 1.250 0.3111 0.01148 0.00623 -0.0344 0.8961 0.9638 1.500 0.3601 0.01112 0.00589 -0.0382 0.8846 0.9724 1.750 0.4102 0.01071 0.00549 -0.0423 0.8701 0.9793 2.000 0.4585 0.01031 0.00511 -0.0460 0.8476 0.9868 2.250 0.5071 0.00995 0.00470 -0.0498 0.8123 0.9933 2.500 0.5541 0.00970 0.00426 -0.0532 0.7443 0.9991 2.750 0.5778 0.00989 0.00396 -0.0520 0.6461 1.0000 3.000 0.5906 0.01040 0.00395 -0.0491 0.5604 1.0000 3.250 0.6040 0.01089 0.00410 -0.0466 0.5041 1.0000 3.500 0.6194 0.01132 0.00428 -0.0443 0.4623 1.0000 3.750 0.6361 0.01173 0.00450 -0.0424 0.4298 1.0000 4.000 0.6541 0.01209 0.00472 -0.0406 0.4027 1.0000 4.250 0.6731 0.01245 0.00496 -0.0391 0.3802 1.0000 4.500 0.6925 0.01283 0.00523 -0.0376 0.3602 1.0000 4.750 0.7120 0.01322 0.00551 -0.0361 0.3417 1.0000 5.000 0.7325 0.01354 0.00582 -0.0348 0.3232 1.0000 5.250 0.7532 0.01388 0.00611 -0.0336 0.3061 1.0000 5.500 0.7743 0.01424 0.00643 -0.0324 0.2904 1.0000 5.750 0.7953 0.01460 0.00676 -0.0313 0.2745 1.0000 6.000 0.8166 0.01498 0.00713 -0.0302 0.2593 1.0000 6.250 0.8380 0.01537 0.00751 -0.0292 0.2444 1.0000 6.500 0.8593 0.01576 0.00787 -0.0281 0.2294 1.0000 6.750 0.8807 0.01614 0.00825 -0.0271 0.2149 1.0000 7.000 0.9023 0.01655 0.00869 -0.0261 0.2017 1.0000 7.250 0.9237 0.01699 0.00914 -0.0251 0.1889 1.0000 7.500 0.9449 0.01745 0.00962 -0.0242 0.1765 1.0000 7.750 0.9657 0.01797 0.01015 -0.0231 0.1646 1.0000 8.000 0.9860 0.01853 0.01071 -0.0220 0.1523 1.0000 8.250 1.0058 0.01912 0.01134 -0.0208 0.1393 1.0000 8.500 1.0249 0.01980 0.01202 -0.0196 0.1263 1.0000 8.750 1.0430 0.02066 0.01286 -0.0182 0.1145 1.0000 9.000 1.0621 0.02144 0.01375 -0.0169 0.1044 1.0000 9.250 1.0799 0.02230 0.01467 -0.0155 0.0950 1.0000 9.500 1.0966 0.02307 0.01544 -0.0141 0.0863 1.0000 9.750 1.1150 0.02352 0.01603 -0.0128 0.0786 1.0000 10.000 1.1309 0.02444 0.01701 -0.0112 0.0726 1.0000 10.250 1.1460 0.02517 0.01781 -0.0096 0.0664 1.0000 10.500 1.1584 0.02628 0.01903 -0.0075 0.0607 1.0000 10.750 1.1691 0.02729 0.02013 -0.0053 0.0546 1.0000 11.000 1.1770 0.02873 0.02172 -0.0028 0.0478 1.0000 11.250 1.1808 0.03029 0.02326 0.0000 0.0416 1.0000 11.500 1.1879 0.03167 0.02490 0.0024 0.0366 1.0000 11.750 1.1911 0.03332 0.02657 0.0049 0.0332 1.0000 12.000 1.1924 0.03563 0.02904 0.0075 0.0306 1.0000 12.250 1.1961 0.03732 0.03094 0.0096 0.0281 1.0000 12.500 1.1983 0.03908 0.03280 0.0114 0.0261 1.0000 12.750 1.1968 0.04144 0.03525 0.0132 0.0246 1.0000 13.000 1.1887 0.04526 0.03922 0.0152 0.0235 1.0000 13.250 1.1856 0.04792 0.04214 0.0164 0.0229 1.0000 13.500 1.1798 0.05111 0.04558 0.0173 0.0223 1.0000 13.750 1.1718 0.05476 0.04947 0.0175 0.0217 1.0000 14.000 1.1621 0.05883 0.05377 0.0171 0.0213 1.0000 14.250 1.1508 0.06339 0.05854 0.0159 0.0209 1.0000 14.500 1.1378 0.06856 0.06391 0.0139 0.0205 1.0000 14.750 1.1223 0.07450 0.07007 0.0110 0.0204 1.0000 15.000 1.1049 0.08122 0.07700 0.0073 0.0203 1.0000 15.250 1.0833 0.08912 0.08512 0.0028 0.0205 1.0000 15.500 1.0579 0.09821 0.09441 -0.0027 0.0208 1.0000 15.750 1.0292 0.10841 0.10480 -0.0089 0.0214 1.0000 16.000 0.9989 0.11940 0.11595 -0.0155 0.0221 1.0000 16.250 0.9667 0.13151 0.12817 -0.0226 0.0228 1.0000