XFOIL Version 6.96 Calculated polar for: BOEING 737 MIDSPAN 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5785 0.08617 0.08334 -0.0103 0.5940 0.0041 -9.000 -0.5855 0.07887 0.07607 -0.0178 0.5929 0.0041 -8.750 -0.5988 0.07211 0.06926 -0.0251 0.5918 0.0041 -8.500 -0.6095 0.06605 0.06310 -0.0279 0.5908 0.0042 -8.250 -0.6138 0.05983 0.05672 -0.0295 0.5900 0.0044 -8.000 -0.6105 0.05456 0.05128 -0.0299 0.5891 0.0045 -7.750 -0.6071 0.04894 0.04545 -0.0298 0.5883 0.0046 -7.500 -0.5982 0.04458 0.04087 -0.0294 0.5875 0.0047 -7.250 -0.5851 0.04091 0.03701 -0.0288 0.5867 0.0048 -7.000 -0.5693 0.03771 0.03361 -0.0281 0.5859 0.0049 -6.000 -0.4973 0.02229 0.01696 -0.0231 0.5832 0.0056 -5.750 -0.4757 0.01897 0.01322 -0.0217 0.5828 0.0061 -5.500 -0.4517 0.01687 0.01078 -0.0209 0.5823 0.0065 -5.250 -0.4264 0.01556 0.00925 -0.0203 0.5819 0.0067 -5.000 -0.4008 0.01458 0.00810 -0.0200 0.5814 0.0068 -4.750 -0.3749 0.01376 0.00716 -0.0196 0.5810 0.0069 -4.500 -0.3495 0.01295 0.00628 -0.0193 0.5805 0.0071 -4.250 -0.3230 0.01257 0.00588 -0.0192 0.5801 0.0073 -4.000 -0.2964 0.01219 0.00548 -0.0191 0.5795 0.0075 -3.750 -0.2702 0.01169 0.00491 -0.0189 0.5789 0.0077 -3.500 -0.2441 0.01118 0.00436 -0.0186 0.5782 0.0078 -3.250 -0.2178 0.01074 0.00387 -0.0183 0.5775 0.0080 -3.000 -0.1914 0.01035 0.00343 -0.0181 0.5767 0.0083 -2.750 -0.1646 0.01003 0.00306 -0.0179 0.5757 0.0090 -2.500 -0.1370 0.00988 0.00286 -0.0179 0.5743 0.0097 -2.250 -0.1105 0.00952 0.00250 -0.0178 0.5728 0.0105 -2.000 -0.0832 0.00932 0.00228 -0.0178 0.5715 0.0115 -1.750 -0.0557 0.00917 0.00210 -0.0178 0.5704 0.0123 -1.250 -0.0002 0.00893 0.00184 -0.0179 0.5684 0.0132 -1.000 0.0274 0.00872 0.00161 -0.0179 0.5674 0.0145 -0.750 0.0553 0.00859 0.00147 -0.0179 0.5658 0.0152 -0.500 0.0833 0.00850 0.00138 -0.0180 0.5637 0.0152 -0.250 0.1113 0.00843 0.00131 -0.0181 0.5607 0.0152 0.000 0.1392 0.00839 0.00125 -0.0182 0.5564 0.0153 0.250 0.1673 0.00832 0.00119 -0.0183 0.5512 0.0154 0.500 0.1955 0.00826 0.00113 -0.0184 0.5457 0.0157 0.750 0.2235 0.00822 0.00109 -0.0185 0.5415 0.0163 1.000 0.2518 0.00816 0.00106 -0.0187 0.5380 0.0172 1.500 0.3083 0.00802 0.00104 -0.0189 0.5238 0.0498 1.750 0.3360 0.00802 0.00094 -0.0190 0.4728 0.0585 2.000 0.3573 0.00706 0.00091 -0.0185 0.4502 0.4869 2.250 0.3834 0.00700 0.00102 -0.0184 0.4349 0.5519 2.500 0.4104 0.00697 0.00110 -0.0184 0.4187 0.5962 2.750 0.4357 0.00700 0.00119 -0.0182 0.3717 0.6570 3.000 0.4566 0.00670 0.00135 -0.0169 0.3399 0.8270 3.250 0.4778 0.00670 0.00155 -0.0153 0.3197 0.9110 3.500 0.5035 0.00689 0.00168 -0.0149 0.2928 0.9230 3.750 0.5293 0.00717 0.00183 -0.0147 0.2567 0.9302 4.000 0.5547 0.00749 0.00201 -0.0144 0.2198 0.9386 4.250 0.5805 0.00775 0.00219 -0.0142 0.1926 0.9467 4.500 0.6063 0.00806 0.00238 -0.0140 0.1638 0.9551 4.750 0.6331 0.00833 0.00257 -0.0140 0.1412 0.9628 5.000 0.6608 0.00863 0.00278 -0.0142 0.1184 0.9695 5.500 0.7186 0.00925 0.00325 -0.0153 0.0815 0.9807 5.750 0.7479 0.00952 0.00349 -0.0160 0.0695 0.9860 6.000 0.7788 0.00983 0.00375 -0.0170 0.0579 0.9904 6.250 0.8085 0.01018 0.00406 -0.0178 0.0452 0.9949 6.500 0.8386 0.01056 0.00438 -0.0187 0.0339 0.9986 6.750 0.8641 0.01092 0.00471 -0.0186 0.0254 1.0000 7.000 0.8872 0.01129 0.00506 -0.0179 0.0190 1.0000 7.250 0.9109 0.01163 0.00540 -0.0174 0.0161 1.0000 7.500 0.9347 0.01200 0.00577 -0.0169 0.0136 1.0000 7.750 0.9592 0.01231 0.00612 -0.0165 0.0128 1.0000 8.000 0.9835 0.01265 0.00650 -0.0161 0.0121 1.0000 8.250 1.0077 0.01301 0.00689 -0.0157 0.0113 1.0000 8.500 1.0315 0.01341 0.00731 -0.0153 0.0103 1.0000 8.750 1.0548 0.01387 0.00779 -0.0148 0.0090 1.0000 9.000 1.0787 0.01426 0.00824 -0.0145 0.0084 1.0000 9.250 1.1027 0.01461 0.00864 -0.0141 0.0077 1.0000 9.500 1.1261 0.01503 0.00910 -0.0137 0.0064 1.0000 9.750 1.1485 0.01555 0.00962 -0.0132 0.0051 1.0000 10.000 1.1706 0.01609 0.01020 -0.0126 0.0043 1.0000 10.250 1.1921 0.01668 0.01084 -0.0120 0.0037 1.0000 10.500 1.2127 0.01737 0.01159 -0.0112 0.0032 1.0000 10.750 1.2334 0.01799 0.01229 -0.0105 0.0031 1.0000 11.000 1.2535 0.01866 0.01304 -0.0097 0.0029 1.0000 11.250 1.2728 0.01937 0.01383 -0.0088 0.0028 1.0000 11.500 1.2912 0.02013 0.01468 -0.0078 0.0027 1.0000 11.750 1.3086 0.02094 0.01558 -0.0068 0.0025 1.0000 12.000 1.3248 0.02180 0.01654 -0.0055 0.0024 1.0000 12.250 1.3394 0.02274 0.01758 -0.0042 0.0023 1.0000 12.500 1.3507 0.02372 0.01866 -0.0023 0.0022 1.0000 12.750 1.3598 0.02480 0.01987 -0.0003 0.0021 1.0000 13.000 1.3667 0.02607 0.02125 0.0017 0.0020 1.0000 13.250 1.3710 0.02759 0.02290 0.0037 0.0019 1.0000 13.500 1.3722 0.02945 0.02490 0.0056 0.0018 1.0000 13.750 1.3699 0.03177 0.02739 0.0071 0.0017 1.0000 14.000 1.3661 0.03448 0.03026 0.0080 0.0017 1.0000 14.250 1.3673 0.03693 0.03284 0.0082 0.0017 1.0000 14.500 1.3667 0.03979 0.03584 0.0079 0.0016 1.0000 14.750 1.3640 0.04311 0.03931 0.0071 0.0016 1.0000 15.000 1.3588 0.04690 0.04324 0.0060 0.0016 1.0000 15.250 1.3508 0.05123 0.04771 0.0045 0.0016 1.0000 15.500 1.3403 0.05595 0.05257 0.0028 0.0016 1.0000 15.750 1.3260 0.06133 0.05810 0.0007 0.0016 1.0000 16.000 1.3086 0.06760 0.06453 -0.0022 0.0016 1.0000 16.250 1.2880 0.07504 0.07212 -0.0060 0.0016 1.0000 16.500 1.2634 0.08361 0.08085 -0.0104 0.0016 1.0000 16.750 1.2362 0.09302 0.09042 -0.0152 0.0016 1.0000 17.000 1.2040 0.10372 0.10126 -0.0206 0.0016 1.0000 17.250 1.1690 0.11510 0.11278 -0.0262 0.0016 1.0000