XFOIL Version 6.96 Calculated polar for: BOEING 737 OUTBOARD 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.5514 0.12309 0.12147 0.0028 1.0000 0.0090 -11.000 -0.5484 0.11867 0.11706 0.0007 1.0000 0.0091 -10.750 -0.5459 0.11427 0.11267 -0.0014 1.0000 0.0091 -10.500 -0.5437 0.10975 0.10816 -0.0037 1.0000 0.0091 -4.250 -0.2990 0.01468 0.00911 -0.0250 0.8072 0.0130 -4.000 -0.2723 0.01371 0.00801 -0.0247 0.8002 0.0129 -3.750 -0.2462 0.01251 0.00672 -0.0242 0.7943 0.0124 -3.500 -0.2204 0.01144 0.00556 -0.0238 0.7882 0.0124 -3.250 -0.1947 0.01074 0.00476 -0.0233 0.7824 0.0127 -3.000 -0.1708 0.00970 0.00366 -0.0227 0.7765 0.0138 -2.750 -0.1441 0.00936 0.00329 -0.0226 0.7702 0.0146 -2.500 -0.1171 0.00907 0.00295 -0.0225 0.7644 0.0155 -2.250 -0.0898 0.00878 0.00263 -0.0224 0.7578 0.0165 -2.000 -0.0628 0.00850 0.00226 -0.0223 0.7516 0.0181 -1.750 -0.0352 0.00821 0.00196 -0.0223 0.7455 0.0211 -1.500 -0.0074 0.00806 0.00177 -0.0224 0.7401 0.0234 -1.250 0.0205 0.00786 0.00154 -0.0224 0.7353 0.0309 -1.000 0.0470 0.00732 0.00138 -0.0224 0.7302 0.1530 -0.750 0.0659 0.00558 0.00110 -0.0217 0.7250 0.6174 -0.500 0.0932 0.00544 0.00110 -0.0216 0.7198 0.6686 -0.250 0.1213 0.00538 0.00108 -0.0217 0.7141 0.6952 0.000 0.1491 0.00536 0.00107 -0.0217 0.7081 0.7166 0.250 0.1774 0.00531 0.00106 -0.0218 0.7009 0.7328 0.500 0.2052 0.00530 0.00105 -0.0218 0.6937 0.7502 0.750 0.2334 0.00525 0.00106 -0.0219 0.6858 0.7660 1.000 0.2613 0.00525 0.00105 -0.0220 0.6771 0.7794 1.250 0.2894 0.00524 0.00105 -0.0221 0.6666 0.7895 1.500 0.3176 0.00522 0.00107 -0.0222 0.6578 0.8008 1.750 0.3456 0.00523 0.00109 -0.0223 0.6495 0.8135 2.000 0.3735 0.00522 0.00112 -0.0223 0.6395 0.8273 2.250 0.4012 0.00523 0.00116 -0.0223 0.6284 0.8423 2.500 0.4286 0.00524 0.00120 -0.0223 0.6169 0.8587 2.750 0.4557 0.00527 0.00125 -0.0221 0.6021 0.8762 3.000 0.4822 0.00532 0.00131 -0.0219 0.5829 0.8943 3.250 0.5082 0.00541 0.00139 -0.0215 0.5582 0.9124 3.500 0.5329 0.00559 0.00149 -0.0209 0.5185 0.9309 3.750 0.5574 0.00590 0.00163 -0.0203 0.4660 0.9495 4.000 0.5837 0.00633 0.00183 -0.0203 0.4054 0.9659 4.250 0.6137 0.00678 0.00205 -0.0212 0.3438 0.9780 4.500 0.6460 0.00713 0.00226 -0.0225 0.3114 0.9868 4.750 0.6787 0.00749 0.00248 -0.0241 0.2778 0.9940 5.000 0.7132 0.00789 0.00269 -0.0260 0.2296 0.9979 5.250 0.7414 0.00829 0.00293 -0.0266 0.1945 1.0000 5.500 0.7642 0.00861 0.00315 -0.0259 0.1723 1.0000 5.750 0.7876 0.00891 0.00337 -0.0253 0.1544 1.0000 6.000 0.8116 0.00921 0.00361 -0.0248 0.1384 1.0000 6.250 0.8359 0.00951 0.00385 -0.0244 0.1206 1.0000 6.500 0.8595 0.00993 0.00415 -0.0240 0.0964 1.0000 6.750 0.8825 0.01043 0.00451 -0.0234 0.0706 1.0000 7.000 0.9051 0.01099 0.00494 -0.0229 0.0472 1.0000 7.250 0.9276 0.01159 0.00543 -0.0223 0.0308 1.0000 7.500 0.9516 0.01201 0.00585 -0.0218 0.0258 1.0000 7.750 0.9744 0.01259 0.00645 -0.0212 0.0215 1.0000 8.000 0.9989 0.01294 0.00684 -0.0209 0.0204 1.0000 8.250 1.0229 0.01334 0.00727 -0.0206 0.0188 1.0000 8.500 1.0455 0.01391 0.00786 -0.0200 0.0170 1.0000 8.750 1.0664 0.01466 0.00869 -0.0192 0.0156 1.0000 9.000 1.0900 0.01506 0.00914 -0.0188 0.0150 1.0000 9.250 1.1130 0.01552 0.00965 -0.0183 0.0140 1.0000 9.500 1.1356 0.01599 0.01016 -0.0178 0.0131 1.0000 9.750 1.1546 0.01682 0.01103 -0.0169 0.0119 1.0000 10.000 1.1725 0.01774 0.01205 -0.0157 0.0112 1.0000 10.250 1.1941 0.01823 0.01260 -0.0151 0.0107 1.0000 10.500 1.2145 0.01882 0.01325 -0.0144 0.0100 1.0000 10.750 1.2342 0.01943 0.01392 -0.0136 0.0095 1.0000 11.000 1.2527 0.02011 0.01464 -0.0127 0.0090 1.0000 11.250 1.2643 0.02133 0.01594 -0.0109 0.0084 1.0000 11.500 1.2675 0.02292 0.01767 -0.0078 0.0080 1.0000 11.750 1.2820 0.02366 0.01850 -0.0065 0.0078 1.0000 12.000 1.2937 0.02463 0.01956 -0.0049 0.0075 1.0000 12.250 1.3041 0.02574 0.02077 -0.0034 0.0073 1.0000 12.500 1.3133 0.02699 0.02213 -0.0019 0.0070 1.0000 12.750 1.3226 0.02826 0.02349 -0.0007 0.0068 1.0000 13.000 1.3325 0.02951 0.02483 0.0003 0.0066 1.0000 13.250 1.3414 0.03089 0.02629 0.0012 0.0063 1.0000 13.500 1.3488 0.03247 0.02794 0.0020 0.0061 1.0000 13.750 1.3518 0.03452 0.03008 0.0028 0.0059 1.0000 14.000 1.3465 0.03750 0.03320 0.0037 0.0058 1.0000 14.250 1.3333 0.04147 0.03736 0.0045 0.0056 1.0000 14.500 1.3164 0.04609 0.04219 0.0048 0.0055 1.0000 14.750 1.3145 0.04919 0.04543 0.0045 0.0055 1.0000 15.000 1.3100 0.05272 0.04909 0.0039 0.0054 1.0000 15.250 1.3027 0.05679 0.05330 0.0029 0.0054 1.0000 15.500 1.2942 0.06125 0.05790 0.0015 0.0053 1.0000 15.750 1.2823 0.06649 0.06330 -0.0005 0.0053 1.0000 16.000 1.2691 0.07234 0.06930 -0.0031 0.0053 1.0000 16.250 1.2540 0.07884 0.07594 -0.0062 0.0053 1.0000 16.500 1.2355 0.08624 0.08350 -0.0100 0.0053 1.0000 16.750 1.2162 0.09414 0.09155 -0.0141 0.0053 1.0000 17.000 1.1942 0.10274 0.10028 -0.0185 0.0053 1.0000 17.250 1.1707 0.11181 0.10949 -0.0232 0.0053 1.0000 17.500 1.1452 0.12144 0.11925 -0.0282 0.0053 1.0000 17.750 1.1201 0.13134 0.12928 -0.0334 0.0054 1.0000 18.000 1.0939 0.14196 0.14003 -0.0391 0.0054 1.0000 18.250 1.0646 0.15380 0.15199 -0.0455 0.0055 1.0000