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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5539 0.08464 0.08310 -0.0166 1.0000 0.0062 -9.000 -0.5621 0.07743 0.07591 -0.0246 1.0000 0.0062 -8.750 -0.5727 0.07143 0.06982 -0.0309 0.9479 0.0061 -8.500 -0.5817 0.06715 0.06533 -0.0318 0.9056 0.0061 -8.250 -0.5841 0.06263 0.06062 -0.0328 0.8824 0.0061 -8.000 -0.5822 0.05812 0.05591 -0.0334 0.8658 0.0062 -7.750 -0.5769 0.05366 0.05124 -0.0336 0.8524 0.0063 -7.500 -0.5687 0.04943 0.04680 -0.0335 0.8415 0.0062 -7.250 -0.5583 0.04518 0.04231 -0.0330 0.8322 0.0060 -7.000 -0.5461 0.04075 0.03762 -0.0322 0.8233 0.0059 -6.750 -0.5323 0.03609 0.03266 -0.0310 0.8154 0.0058 -6.500 -0.5172 0.03111 0.02731 -0.0295 0.8079 0.0060 -6.250 -0.5018 0.02451 0.02017 -0.0271 0.8015 0.0065 -6.000 -0.4835 0.01894 0.01403 -0.0251 0.7953 0.0067 -5.750 -0.4600 0.01680 0.01157 -0.0244 0.7895 0.0068 -5.500 -0.4352 0.01535 0.00990 -0.0239 0.7833 0.0068 -5.000 -0.3833 0.01371 0.00796 -0.0234 0.7711 0.0069 -4.750 -0.3584 0.01259 0.00668 -0.0229 0.7645 0.0070 -4.500 -0.3327 0.01186 0.00584 -0.0226 0.7583 0.0070 -4.250 -0.3072 0.01119 0.00508 -0.0223 0.7522 0.0070 -4.000 -0.2815 0.01062 0.00442 -0.0220 0.7466 0.0070 -3.750 -0.2555 0.01010 0.00382 -0.0217 0.7410 0.0071 -3.500 -0.2293 0.00966 0.00330 -0.0215 0.7354 0.0072 -3.250 -0.2025 0.00930 0.00289 -0.0214 0.7302 0.0073 -3.000 -0.1753 0.00902 0.00255 -0.0214 0.7240 0.0075 -2.500 -0.1202 0.00861 0.00207 -0.0214 0.7128 0.0082 -2.250 -0.0924 0.00846 0.00189 -0.0215 0.7058 0.0090 -2.000 -0.0646 0.00831 0.00172 -0.0216 0.6993 0.0107 -1.750 -0.0365 0.00820 0.00160 -0.0217 0.6923 0.0133 -1.500 -0.0084 0.00811 0.00148 -0.0218 0.6870 0.0152 -1.250 0.0198 0.00800 0.00138 -0.0220 0.6820 0.0178 -1.000 0.0480 0.00792 0.00128 -0.0221 0.6770 0.0198 -0.750 0.0762 0.00783 0.00121 -0.0223 0.6718 0.0264 -0.500 0.1040 0.00764 0.00115 -0.0225 0.6658 0.0672 -0.250 0.1242 0.00593 0.00086 -0.0221 0.6596 0.5493 0.000 0.1515 0.00575 0.00085 -0.0221 0.6505 0.6093 0.250 0.1793 0.00569 0.00084 -0.0222 0.6408 0.6418 0.500 0.2072 0.00566 0.00085 -0.0222 0.6299 0.6670 0.750 0.2354 0.00567 0.00085 -0.0224 0.6178 0.6806 1.000 0.2632 0.00565 0.00087 -0.0224 0.6033 0.7043 1.250 0.2908 0.00570 0.00088 -0.0225 0.5821 0.7203 1.500 0.3185 0.00581 0.00091 -0.0226 0.5552 0.7268 1.750 0.3463 0.00591 0.00095 -0.0227 0.5314 0.7334 2.000 0.3738 0.00604 0.00100 -0.0228 0.5038 0.7411 2.250 0.4008 0.00625 0.00109 -0.0228 0.4665 0.7486 2.500 0.4274 0.00649 0.00120 -0.0228 0.4258 0.7571 2.750 0.4543 0.00670 0.00132 -0.0228 0.3925 0.7663 3.000 0.4805 0.00699 0.00146 -0.0228 0.3435 0.7770 3.250 0.5069 0.00723 0.00161 -0.0227 0.3149 0.7893 3.500 0.5338 0.00738 0.00176 -0.0227 0.2985 0.8024 3.750 0.5606 0.00752 0.00190 -0.0227 0.2806 0.8170 4.000 0.5872 0.00768 0.00203 -0.0226 0.2598 0.8334 4.250 0.6131 0.00789 0.00219 -0.0225 0.2297 0.8505 4.500 0.6377 0.00822 0.00242 -0.0221 0.1923 0.8691 4.750 0.6628 0.00846 0.00263 -0.0218 0.1693 0.8884 5.250 0.7120 0.00893 0.00304 -0.0208 0.1320 0.9290 5.500 0.7374 0.00916 0.00327 -0.0205 0.1145 0.9499 5.750 0.7653 0.00951 0.00353 -0.0209 0.0925 0.9684 6.000 0.7962 0.00987 0.00381 -0.0220 0.0739 0.9828 6.250 0.8267 0.01027 0.00414 -0.0230 0.0568 0.9949 6.500 0.8541 0.01067 0.00446 -0.0234 0.0429 1.0000 6.750 0.8781 0.01106 0.00479 -0.0230 0.0317 1.0000 7.000 0.9023 0.01145 0.00514 -0.0226 0.0241 1.0000 7.250 0.9269 0.01178 0.00548 -0.0223 0.0209 1.0000 7.500 0.9513 0.01215 0.00585 -0.0220 0.0181 1.0000 7.750 0.9759 0.01248 0.00621 -0.0217 0.0168 1.0000 8.000 1.0006 0.01281 0.00657 -0.0215 0.0157 1.0000 8.250 1.0247 0.01319 0.00696 -0.0211 0.0144 1.0000 8.500 1.0484 0.01361 0.00740 -0.0208 0.0131 1.0000 8.750 1.0714 0.01411 0.00794 -0.0203 0.0120 1.0000 9.000 1.0953 0.01447 0.00835 -0.0199 0.0116 1.0000 9.250 1.1189 0.01487 0.00879 -0.0196 0.0111 1.0000 9.500 1.1421 0.01529 0.00925 -0.0192 0.0105 1.0000 9.750 1.1649 0.01574 0.00974 -0.0187 0.0098 1.0000 10.000 1.1870 0.01623 0.01025 -0.0182 0.0090 1.0000 10.250 1.2077 0.01685 0.01092 -0.0175 0.0082 1.0000 10.500 1.2296 0.01731 0.01143 -0.0170 0.0079 1.0000 10.750 1.2508 0.01782 0.01200 -0.0163 0.0074 1.0000 11.000 1.2713 0.01837 0.01260 -0.0156 0.0069 1.0000 11.250 1.2910 0.01895 0.01322 -0.0149 0.0064 1.0000 11.500 1.3096 0.01960 0.01392 -0.0139 0.0059 1.0000 11.750 1.3259 0.02040 0.01478 -0.0127 0.0055 1.0000 12.000 1.3414 0.02109 0.01555 -0.0113 0.0053 1.0000 12.250 1.3553 0.02183 0.01637 -0.0098 0.0051 1.0000 12.500 1.3682 0.02266 0.01728 -0.0082 0.0049 1.0000 12.750 1.3804 0.02356 0.01826 -0.0067 0.0047 1.0000 13.000 1.3918 0.02455 0.01933 -0.0053 0.0045 1.0000 13.250 1.4025 0.02563 0.02049 -0.0040 0.0043 1.0000 13.500 1.4123 0.02683 0.02176 -0.0028 0.0041 1.0000 13.750 1.4209 0.02816 0.02319 -0.0016 0.0039 1.0000 14.000 1.4270 0.02977 0.02489 -0.0005 0.0037 1.0000 14.250 1.4300 0.03171 0.02695 0.0006 0.0036 1.0000 14.500 1.4342 0.03362 0.02898 0.0015 0.0035 1.0000 14.750 1.4388 0.03555 0.03101 0.0021 0.0034 1.0000 15.000 1.4417 0.03772 0.03329 0.0026 0.0034 1.0000 15.250 1.4426 0.04016 0.03586 0.0029 0.0033 1.0000 15.500 1.4418 0.04287 0.03869 0.0031 0.0033 1.0000 15.750 1.4398 0.04583 0.04177 0.0030 0.0032 1.0000 16.000 1.4353 0.04918 0.04525 0.0027 0.0032 1.0000 16.250 1.4287 0.05295 0.04915 0.0020 0.0031 1.0000 16.500 1.4202 0.05717 0.05351 0.0009 0.0031 1.0000 16.750 1.4090 0.06202 0.05850 -0.0006 0.0031 1.0000 17.000 1.3957 0.06756 0.06419 -0.0028 0.0031 1.0000 17.250 1.3800 0.07381 0.07059 -0.0056 0.0030 1.0000 17.500 1.3606 0.08100 0.07792 -0.0090 0.0030 1.0000 17.750 1.3369 0.08932 0.08641 -0.0131 0.0030 1.0000 18.000 1.3096 0.09857 0.09582 -0.0177 0.0030 1.0000 18.250 1.2785 0.10864 0.10604 -0.0227 0.0031 1.0000 18.500 1.2453 0.11928 0.11681 -0.0280 0.0031 1.0000