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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5304 0.08656 0.08442 -0.0178 1.0000 0.0153 -8.750 -0.5351 0.08031 0.07819 -0.0243 1.0000 0.0154 -8.500 -0.5451 0.07481 0.07265 -0.0297 1.0000 0.0153 -8.250 -0.5518 0.07043 0.06821 -0.0319 1.0000 0.0155 -8.000 -0.5526 0.06608 0.06378 -0.0335 1.0000 0.0157 -7.750 -0.5497 0.06191 0.05948 -0.0345 1.0000 0.0161 -7.500 -0.5402 0.05810 0.05547 -0.0345 1.0000 0.0169 -7.250 -0.5319 0.05513 0.05232 -0.0335 1.0000 0.0171 -7.000 -0.5121 0.05121 0.04817 -0.0350 0.9912 0.0172 -6.750 -0.4887 0.04709 0.04377 -0.0369 0.9790 0.0173 -6.500 -0.4776 0.04006 0.03653 -0.0387 0.9643 0.0180 -6.250 -0.4578 0.03750 0.03384 -0.0391 0.9492 0.0185 -6.000 -0.4399 0.03533 0.03151 -0.0385 0.9340 0.0191 -5.750 -0.4216 0.03320 0.02915 -0.0374 0.9203 0.0200 -5.500 -0.4007 0.03110 0.02677 -0.0359 0.9084 0.0219 -5.250 -0.3738 0.03132 0.02655 -0.0339 0.8979 0.0235 -5.000 -0.3598 0.02580 0.02077 -0.0332 0.8877 0.0251 -4.750 -0.3372 0.02435 0.01920 -0.0327 0.8790 0.0263 -4.500 -0.3131 0.02311 0.01777 -0.0321 0.8707 0.0284 -4.250 -0.2835 0.02482 0.01919 -0.0311 0.8627 0.0319 -4.000 -0.2636 0.02007 0.01427 -0.0308 0.8559 0.0350 -3.750 -0.2378 0.01898 0.01306 -0.0305 0.8486 0.0373 -3.500 -0.2074 0.01498 0.00857 -0.0283 0.8425 0.0212 -3.250 -0.1814 0.01349 0.00693 -0.0275 0.8358 0.0205 -3.000 -0.1559 0.01259 0.00593 -0.0269 0.8287 0.0210 -2.750 -0.1305 0.01190 0.00517 -0.0263 0.8223 0.0218 -2.500 -0.1041 0.01151 0.00473 -0.0260 0.8156 0.0232 -2.250 -0.0801 0.01069 0.00382 -0.0253 0.8098 0.0252 -2.000 -0.0538 0.01024 0.00333 -0.0251 0.8032 0.0275 -1.750 -0.0270 0.00995 0.00298 -0.0248 0.7975 0.0309 -1.500 -0.0002 0.00961 0.00261 -0.0247 0.7909 0.0381 -1.250 0.0261 0.00914 0.00227 -0.0244 0.7841 0.0939 -1.000 0.0398 0.00696 0.00201 -0.0227 0.7778 0.6762 -0.750 0.0662 0.00686 0.00201 -0.0223 0.7717 0.7179 -0.250 0.1196 0.00676 0.00201 -0.0216 0.7605 0.7722 0.000 0.1466 0.00673 0.00200 -0.0213 0.7550 0.7935 0.250 0.1735 0.00672 0.00202 -0.0210 0.7499 0.8114 0.500 0.2009 0.00669 0.00202 -0.0209 0.7436 0.8258 0.750 0.2283 0.00669 0.00199 -0.0207 0.7375 0.8378 1.000 0.2557 0.00664 0.00200 -0.0206 0.7293 0.8493 1.250 0.2827 0.00663 0.00198 -0.0204 0.7213 0.8618 1.500 0.3096 0.00660 0.00198 -0.0201 0.7119 0.8757 1.750 0.3360 0.00658 0.00198 -0.0197 0.7021 0.8910 2.000 0.3622 0.00658 0.00199 -0.0192 0.6927 0.9072 2.250 0.3886 0.00657 0.00204 -0.0188 0.6839 0.9241 2.500 0.4158 0.00659 0.00208 -0.0185 0.6755 0.9409 2.750 0.4452 0.00663 0.00211 -0.0188 0.6653 0.9560 3.000 0.4785 0.00666 0.00216 -0.0200 0.6532 0.9676 3.250 0.5140 0.00672 0.00222 -0.0217 0.6397 0.9767 3.500 0.5496 0.00679 0.00227 -0.0235 0.6229 0.9853 3.750 0.5875 0.00687 0.00233 -0.0259 0.5993 0.9910 4.000 0.6247 0.00703 0.00240 -0.0282 0.5644 0.9965 4.250 0.6568 0.00731 0.00250 -0.0295 0.5117 1.0000 4.500 0.6769 0.00773 0.00266 -0.0283 0.4517 1.0000 4.750 0.6974 0.00820 0.00289 -0.0273 0.3973 1.0000 5.250 0.7379 0.00931 0.00351 -0.0252 0.2957 1.0000 5.500 0.7604 0.00970 0.00378 -0.0245 0.2596 1.0000 5.750 0.7829 0.01015 0.00405 -0.0238 0.2205 1.0000 6.000 0.8057 0.01061 0.00438 -0.0232 0.1914 1.0000 6.250 0.8288 0.01104 0.00473 -0.0227 0.1680 1.0000 6.500 0.8523 0.01146 0.00508 -0.0223 0.1474 1.0000 6.750 0.8756 0.01190 0.00543 -0.0218 0.1248 1.0000 7.000 0.8980 0.01245 0.00585 -0.0212 0.0953 1.0000 7.250 0.9181 0.01327 0.00646 -0.0203 0.0596 1.0000 7.500 0.9381 0.01413 0.00718 -0.0194 0.0397 1.0000 7.750 0.9601 0.01476 0.00784 -0.0187 0.0337 1.0000 8.000 0.9791 0.01571 0.00883 -0.0175 0.0290 1.0000 8.250 1.0018 0.01621 0.00941 -0.0169 0.0270 1.0000 8.500 1.0231 0.01686 0.01012 -0.0162 0.0249 1.0000 8.750 1.0415 0.01779 0.01109 -0.0150 0.0229 1.0000 9.000 1.0566 0.01904 0.01245 -0.0135 0.0213 1.0000 9.250 1.0774 0.01966 0.01315 -0.0127 0.0200 1.0000 9.500 1.0960 0.02048 0.01407 -0.0117 0.0188 1.0000 9.750 1.1135 0.02137 0.01502 -0.0105 0.0177 1.0000 10.000 1.1273 0.02263 0.01633 -0.0090 0.0167 1.0000 10.250 1.1345 0.02488 0.01873 -0.0066 0.0157 1.0000 10.500 1.1511 0.02554 0.01951 -0.0054 0.0150 1.0000 10.750 1.1648 0.02648 0.02056 -0.0038 0.0142 1.0000 11.000 1.1767 0.02759 0.02179 -0.0022 0.0135 1.0000 11.250 1.1873 0.02883 0.02313 -0.0006 0.0129 1.0000 11.500 1.1966 0.03019 0.02458 0.0010 0.0125 1.0000 11.750 1.2034 0.03192 0.02639 0.0025 0.0120 1.0000 12.000 1.2039 0.03484 0.02949 0.0046 0.0116 1.0000 12.250 1.2011 0.03814 0.03304 0.0066 0.0113 1.0000 12.500 1.2033 0.04013 0.03523 0.0078 0.0111 1.0000 12.750 1.2030 0.04256 0.03786 0.0089 0.0110 1.0000 13.000 1.1998 0.04542 0.04094 0.0097 0.0108 1.0000 13.250 1.1934 0.04875 0.04448 0.0102 0.0107 1.0000 13.500 1.1845 0.05253 0.04848 0.0103 0.0105 1.0000 13.750 1.1726 0.05683 0.05299 0.0099 0.0105 1.0000 14.000 1.1585 0.06167 0.05804 0.0088 0.0104 1.0000 14.250 1.1419 0.06718 0.06376 0.0070 0.0104 1.0000 14.500 1.1234 0.07340 0.07017 0.0043 0.0104 1.0000 14.750 1.1033 0.08043 0.07739 0.0007 0.0104 1.0000 15.000 1.0821 0.08844 0.08558 -0.0039 0.0105 1.0000 15.250 1.0593 0.09744 0.09475 -0.0094 0.0106 1.0000 15.500 1.0354 0.10745 0.10492 -0.0156 0.0107 1.0000 15.750 1.0088 0.11850 0.11610 -0.0222 0.0109 1.0000 16.000 0.9781 0.13111 0.12882 -0.0295 0.0111 1.0000 16.250 0.8176 0.11444 0.11209 -0.0041 0.0116 1.0000