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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5187 0.08084 0.07925 -0.0402 1.0000 0.0080 -9.500 -0.5473 0.07319 0.07159 -0.0451 1.0000 0.0078 -9.250 -0.5826 0.06929 0.06766 -0.0442 1.0000 0.0077 -9.000 -0.6085 0.06586 0.06416 -0.0432 0.9986 0.0077 -8.750 -0.6040 0.06065 0.05881 -0.0473 0.9958 0.0078 -8.500 -0.5974 0.05622 0.05424 -0.0497 0.9936 0.0081 -8.250 -0.5885 0.05206 0.04991 -0.0510 0.9906 0.0084 -8.000 -0.5668 0.04741 0.04498 -0.0516 0.9887 0.0100 -5.250 -0.3175 0.01467 0.00951 -0.0533 0.9679 0.0104 -5.000 -0.2861 0.01374 0.00850 -0.0540 0.9667 0.0102 -4.750 -0.2581 0.01202 0.00669 -0.0542 0.9652 0.0105 -4.500 -0.2391 0.01118 0.00581 -0.0524 0.9599 0.0108 -4.250 -0.2133 0.01053 0.00511 -0.0520 0.9564 0.0110 -4.000 -0.1847 0.00994 0.00448 -0.0522 0.9531 0.0113 -3.750 -0.1623 0.00951 0.00401 -0.0509 0.9463 0.0115 -3.500 -0.1357 0.00912 0.00359 -0.0505 0.9406 0.0121 -3.250 -0.1098 0.00879 0.00321 -0.0500 0.9357 0.0126 -3.000 -0.0848 0.00847 0.00285 -0.0494 0.9303 0.0128 -2.750 -0.0578 0.00819 0.00252 -0.0491 0.9257 0.0133 -2.500 -0.0307 0.00798 0.00227 -0.0488 0.9211 0.0141 -2.250 -0.0050 0.00771 0.00201 -0.0483 0.9150 0.0231 -2.000 0.0104 0.00593 0.00150 -0.0467 0.9091 0.4060 -1.750 0.0331 0.00548 0.00143 -0.0458 0.9024 0.5202 -1.500 0.0600 0.00531 0.00135 -0.0455 0.8961 0.5608 -1.250 0.0863 0.00520 0.00129 -0.0451 0.8864 0.5878 -1.000 0.1125 0.00507 0.00123 -0.0447 0.8742 0.6207 -0.500 0.1663 0.00497 0.00113 -0.0441 0.8492 0.6584 -0.250 0.1933 0.00495 0.00110 -0.0438 0.8352 0.6715 0.000 0.2199 0.00494 0.00106 -0.0435 0.8171 0.6821 0.250 0.2458 0.00498 0.00103 -0.0430 0.7910 0.6927 0.500 0.2697 0.00509 0.00101 -0.0420 0.7471 0.7042 0.750 0.2914 0.00532 0.00103 -0.0407 0.6891 0.7168 1.000 0.3119 0.00564 0.00111 -0.0391 0.6140 0.7309 1.250 0.3327 0.00600 0.00121 -0.0378 0.5412 0.7468 1.500 0.3556 0.00626 0.00132 -0.0368 0.4881 0.7650 1.750 0.3796 0.00647 0.00141 -0.0361 0.4454 0.7846 2.000 0.4042 0.00663 0.00150 -0.0356 0.4108 0.8047 2.250 0.4286 0.00678 0.00160 -0.0349 0.3791 0.8261 2.500 0.4531 0.00692 0.00171 -0.0343 0.3536 0.8496 2.750 0.4778 0.00701 0.00182 -0.0336 0.3348 0.8765 3.000 0.5024 0.00711 0.00193 -0.0329 0.3184 0.9044 3.250 0.5275 0.00723 0.00206 -0.0323 0.3026 0.9305 3.500 0.5546 0.00738 0.00219 -0.0321 0.2876 0.9517 3.750 0.5850 0.00756 0.00233 -0.0328 0.2734 0.9667 4.000 0.6171 0.00776 0.00248 -0.0339 0.2585 0.9773 4.250 0.6498 0.00798 0.00263 -0.0352 0.2423 0.9854 4.500 0.6858 0.00820 0.00278 -0.0373 0.2267 0.9895 4.750 0.7206 0.00843 0.00295 -0.0390 0.2107 0.9938 5.000 0.7560 0.00867 0.00312 -0.0410 0.1937 0.9966 5.250 0.7915 0.00891 0.00331 -0.0430 0.1797 0.9993 5.500 0.8164 0.00913 0.00348 -0.0427 0.1678 1.0000 5.750 0.8375 0.00933 0.00365 -0.0414 0.1576 1.0000 6.000 0.8591 0.00953 0.00383 -0.0403 0.1479 1.0000 6.250 0.8806 0.00975 0.00402 -0.0391 0.1378 1.0000 6.500 0.9020 0.01001 0.00422 -0.0380 0.1273 1.0000 6.750 0.9242 0.01024 0.00445 -0.0370 0.1201 1.0000 7.000 0.9465 0.01049 0.00469 -0.0360 0.1123 1.0000 7.250 0.9689 0.01078 0.00494 -0.0352 0.1042 1.0000 7.500 0.9922 0.01102 0.00520 -0.0344 0.0964 1.0000 7.750 1.0148 0.01135 0.00548 -0.0336 0.0845 1.0000 8.000 1.0363 0.01180 0.00583 -0.0327 0.0686 1.0000 8.250 1.0585 0.01221 0.00620 -0.0319 0.0596 1.0000 8.500 1.0804 0.01266 0.00662 -0.0310 0.0518 1.0000 8.750 1.1040 0.01294 0.00694 -0.0304 0.0485 1.0000 9.000 1.1260 0.01339 0.00736 -0.0296 0.0427 1.0000 9.250 1.1488 0.01374 0.00775 -0.0289 0.0392 1.0000 9.500 1.1708 0.01417 0.00817 -0.0282 0.0354 1.0000 9.750 1.1926 0.01461 0.00863 -0.0274 0.0315 1.0000 10.000 1.2150 0.01498 0.00902 -0.0267 0.0282 1.0000 10.250 1.2355 0.01551 0.00954 -0.0257 0.0225 1.0000 10.500 1.2533 0.01628 0.01023 -0.0244 0.0144 1.0000 10.750 1.2719 0.01696 0.01095 -0.0231 0.0114 1.0000 11.000 1.2892 0.01772 0.01175 -0.0216 0.0097 1.0000 11.250 1.3058 0.01850 0.01262 -0.0200 0.0085 1.0000 11.500 1.3230 0.01912 0.01332 -0.0185 0.0079 1.0000 11.750 1.3379 0.01983 0.01410 -0.0167 0.0073 1.0000 12.000 1.3501 0.02070 0.01505 -0.0145 0.0066 1.0000 12.250 1.3534 0.02218 0.01668 -0.0111 0.0059 1.0000 12.500 1.3674 0.02288 0.01746 -0.0093 0.0057 1.0000 12.750 1.3795 0.02370 0.01838 -0.0074 0.0054 1.0000 13.000 1.3901 0.02462 0.01939 -0.0054 0.0051 1.0000 13.250 1.3990 0.02567 0.02053 -0.0034 0.0048 1.0000 13.500 1.4070 0.02680 0.02174 -0.0013 0.0045 1.0000 13.750 1.4116 0.02819 0.02323 0.0009 0.0043 1.0000 14.000 1.4107 0.03005 0.02522 0.0034 0.0041 1.0000 14.250 1.4017 0.03267 0.02800 0.0061 0.0039 1.0000 14.500 1.3860 0.03609 0.03162 0.0084 0.0038 1.0000 14.750 1.3859 0.03840 0.03405 0.0093 0.0037 1.0000 15.000 1.3841 0.04107 0.03684 0.0098 0.0037 1.0000 15.250 1.3794 0.04433 0.04023 0.0098 0.0036 1.0000 15.500 1.3705 0.04845 0.04450 0.0089 0.0036 1.0000 15.750 1.3594 0.05341 0.04961 0.0071 0.0036 1.0000 16.000 1.3447 0.05955 0.05591 0.0040 0.0035 1.0000 16.250 1.3256 0.06688 0.06341 0.0001 0.0035 1.0000 16.500 1.3019 0.07521 0.07190 -0.0043 0.0035 1.0000 16.750 1.2745 0.08401 0.08086 -0.0086 0.0036 1.0000 17.000 1.2436 0.09332 0.09031 -0.0130 0.0036 1.0000