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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5155 0.09244 0.08766 -0.0225 1.0000 0.0485 -8.750 -0.5216 0.08704 0.08229 -0.0283 1.0000 0.0492 -8.500 -0.5332 0.08279 0.07800 -0.0322 1.0000 0.0499 -8.250 -0.5474 0.08000 0.07502 -0.0347 1.0000 0.0509 -8.000 -0.5530 0.07738 0.07218 -0.0352 1.0000 0.0513 -7.750 -0.5526 0.07457 0.06915 -0.0349 1.0000 0.0515 -7.250 -0.5397 0.06341 0.05820 -0.0349 1.0000 0.0540 -7.000 -0.5324 0.06034 0.05514 -0.0341 1.0000 0.0562 -6.750 -0.5283 0.05765 0.05237 -0.0326 1.0000 0.0586 -6.500 -0.5268 0.05528 0.04987 -0.0304 1.0000 0.0608 -6.250 -0.5269 0.05331 0.04770 -0.0274 0.9998 0.0627 -6.000 -0.4979 0.04681 0.04052 -0.0287 0.9903 0.0410 -5.500 -0.4364 0.03869 0.03130 -0.0306 0.9753 0.0279 -5.250 -0.4069 0.03544 0.02773 -0.0321 0.9688 0.0272 -5.000 -0.3778 0.03272 0.02466 -0.0329 0.9612 0.0267 -4.750 -0.3472 0.03027 0.02184 -0.0337 0.9542 0.0263 -4.500 -0.3150 0.02804 0.01925 -0.0346 0.9481 0.0261 -4.250 -0.2846 0.02613 0.01701 -0.0349 0.9406 0.0262 -4.000 -0.2512 0.02435 0.01495 -0.0357 0.9354 0.0265 -3.750 -0.2214 0.02310 0.01345 -0.0358 0.9275 0.0279 -3.500 -0.1904 0.02162 0.01192 -0.0365 0.9220 0.0304 -3.250 -0.1631 0.02059 0.01084 -0.0364 0.9140 0.0324 -3.000 -0.1342 0.01954 0.00974 -0.0365 0.9083 0.0344 -2.750 -0.1094 0.01888 0.00901 -0.0358 0.9000 0.0382 -2.250 -0.0601 0.01746 0.00748 -0.0347 0.8857 0.0484 -2.000 -0.0335 0.01691 0.00681 -0.0345 0.8799 0.0602 -1.750 -0.0092 0.01636 0.00623 -0.0339 0.8720 0.0837 -1.500 -0.0013 0.01392 0.00618 -0.0303 0.8658 0.6821 -1.250 0.0145 0.01396 0.00656 -0.0262 0.8584 0.7900 -1.000 0.0340 0.01417 0.00683 -0.0226 0.8527 0.8487 -0.750 0.0603 0.01428 0.00687 -0.0215 0.8464 0.8711 -0.500 0.0887 0.01428 0.00674 -0.0216 0.8400 0.8812 -0.250 0.1178 0.01427 0.00662 -0.0218 0.8338 0.8912 0.000 0.1478 0.01427 0.00653 -0.0222 0.8262 0.9004 0.250 0.1778 0.01425 0.00643 -0.0226 0.8187 0.9108 0.500 0.2079 0.01423 0.00634 -0.0230 0.8100 0.9219 0.750 0.2409 0.01423 0.00628 -0.0240 0.8016 0.9316 1.000 0.2747 0.01422 0.00622 -0.0252 0.7941 0.9416 1.250 0.3089 0.01424 0.00623 -0.0267 0.7858 0.9521 1.500 0.3444 0.01422 0.00618 -0.0283 0.7785 0.9621 1.750 0.3805 0.01425 0.00622 -0.0302 0.7694 0.9723 2.000 0.4179 0.01421 0.00618 -0.0323 0.7613 0.9815 2.250 0.4553 0.01421 0.00622 -0.0346 0.7510 0.9912 2.500 0.4908 0.01417 0.00621 -0.0364 0.7389 1.0000 2.750 0.5109 0.01413 0.00616 -0.0349 0.7246 1.0000 3.000 0.5315 0.01408 0.00609 -0.0334 0.7082 1.0000 3.250 0.5529 0.01406 0.00610 -0.0321 0.6919 1.0000 3.500 0.5749 0.01411 0.00616 -0.0310 0.6772 1.0000 3.750 0.5973 0.01415 0.00623 -0.0299 0.6611 1.0000 4.000 0.6201 0.01420 0.00631 -0.0289 0.6435 1.0000 4.250 0.6426 0.01429 0.00648 -0.0278 0.6218 1.0000 4.500 0.6654 0.01437 0.00657 -0.0267 0.5969 1.0000 4.750 0.6879 0.01448 0.00669 -0.0256 0.5650 1.0000 5.000 0.7100 0.01465 0.00677 -0.0243 0.5232 1.0000 5.250 0.7307 0.01498 0.00694 -0.0229 0.4705 1.0000 5.500 0.7500 0.01553 0.00721 -0.0214 0.4147 1.0000 5.750 0.7688 0.01619 0.00765 -0.0200 0.3618 1.0000 6.000 0.7872 0.01695 0.00816 -0.0187 0.3209 1.0000 6.250 0.8068 0.01767 0.00878 -0.0176 0.2877 1.0000 6.500 0.8271 0.01832 0.00942 -0.0167 0.2532 1.0000 6.750 0.8463 0.01906 0.01002 -0.0156 0.2173 1.0000 7.000 0.8648 0.01989 0.01069 -0.0146 0.1827 1.0000 7.250 0.8834 0.02073 0.01143 -0.0136 0.1530 1.0000 7.500 0.9023 0.02158 0.01225 -0.0127 0.1242 1.0000 7.750 0.9202 0.02255 0.01311 -0.0116 0.0952 1.0000 8.000 0.9367 0.02369 0.01417 -0.0104 0.0746 1.0000 8.250 0.9521 0.02496 0.01542 -0.0090 0.0621 1.0000 8.500 0.9662 0.02631 0.01675 -0.0075 0.0537 1.0000 8.750 0.9819 0.02748 0.01805 -0.0061 0.0471 1.0000 9.000 0.9932 0.02904 0.01964 -0.0044 0.0434 1.0000 9.250 1.0078 0.03040 0.02122 -0.0029 0.0408 1.0000 9.500 1.0219 0.03186 0.02284 -0.0014 0.0381 1.0000 9.750 1.0347 0.03329 0.02436 0.0000 0.0354 1.0000 10.000 1.0442 0.03523 0.02630 0.0016 0.0330 1.0000 10.250 1.0583 0.03696 0.02830 0.0031 0.0316 1.0000 10.500 1.0713 0.03899 0.03058 0.0045 0.0303 1.0000 10.750 1.0813 0.04101 0.03286 0.0060 0.0287 1.0000 11.000 1.0881 0.04292 0.03500 0.0076 0.0271 1.0000 11.250 1.0928 0.04490 0.03710 0.0090 0.0258 1.0000 11.500 1.0961 0.04745 0.03978 0.0103 0.0248 1.0000 11.750 1.0962 0.05083 0.04337 0.0117 0.0242 1.0000 12.000 1.0921 0.05396 0.04685 0.0129 0.0238 1.0000 12.250 1.0842 0.05749 0.05071 0.0138 0.0236 1.0000 12.500 1.0731 0.06144 0.05496 0.0141 0.0233 1.0000 12.750 1.0592 0.06585 0.05967 0.0138 0.0231 1.0000 13.000 1.0428 0.07082 0.06491 0.0126 0.0230 1.0000 13.250 1.0244 0.07645 0.07078 0.0105 0.0230 1.0000 13.500 1.0042 0.08284 0.07739 0.0074 0.0230 1.0000 13.750 0.9826 0.09014 0.08488 0.0033 0.0232 1.0000 14.000 0.9598 0.09847 0.09337 -0.0019 0.0234 1.0000 14.250 0.9365 0.10790 0.10293 -0.0080 0.0237 1.0000 14.500 0.9125 0.11855 0.11366 -0.0148 0.0240 1.0000 14.750 0.8894 0.12979 0.12494 -0.0214 0.0242 1.0000