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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4425 0.07825 0.07622 -0.0199 1.0000 0.0091 -8.750 -0.5544 0.07986 0.07777 -0.0190 1.0000 0.0084 -8.500 -0.5680 0.07283 0.07071 -0.0265 1.0000 0.0079 -8.250 -0.5766 0.06618 0.06394 -0.0304 0.9816 0.0075 -8.000 -0.5740 0.06026 0.05784 -0.0334 0.9625 0.0074 -7.750 -0.5674 0.05582 0.05323 -0.0345 0.9438 0.0075 -7.500 -0.5598 0.05174 0.04894 -0.0346 0.9244 0.0075 -7.250 -0.5510 0.04805 0.04502 -0.0338 0.8943 0.0076 -7.000 -0.5442 0.04599 0.04235 -0.0314 0.7577 0.0081 -6.750 -0.5301 0.04272 0.03867 -0.0305 0.7126 0.0088 -6.500 -0.5148 0.03898 0.03458 -0.0296 0.6913 0.0089 -6.250 -0.4985 0.03530 0.03056 -0.0285 0.6773 0.0085 -6.000 -0.4805 0.03141 0.02630 -0.0272 0.6674 0.0082 -5.750 -0.4608 0.02756 0.02204 -0.0258 0.6592 0.0081 -5.500 -0.4395 0.02378 0.01782 -0.0243 0.6528 0.0083 -5.250 -0.4161 0.02098 0.01461 -0.0231 0.6470 0.0087 -4.750 -0.3655 0.01785 0.01081 -0.0218 0.6381 0.0094 -4.500 -0.3395 0.01694 0.00964 -0.0214 0.6344 0.0100 -4.250 -0.3141 0.01587 0.00854 -0.0212 0.6312 0.0104 -4.000 -0.2882 0.01495 0.00750 -0.0208 0.6285 0.0104 -3.750 -0.2623 0.01415 0.00659 -0.0204 0.6261 0.0105 -3.500 -0.2366 0.01345 0.00582 -0.0201 0.6241 0.0107 -3.250 -0.2108 0.01282 0.00515 -0.0197 0.6221 0.0110 -3.000 -0.1851 0.01228 0.00455 -0.0193 0.6203 0.0113 -2.750 -0.1591 0.01181 0.00401 -0.0190 0.6183 0.0120 -2.500 -0.1327 0.01144 0.00359 -0.0188 0.6163 0.0128 -2.250 -0.1064 0.01106 0.00315 -0.0185 0.6145 0.0137 -1.750 -0.0534 0.01035 0.00235 -0.0182 0.6108 0.0166 -1.500 -0.0261 0.01015 0.00211 -0.0182 0.6082 0.0182 -1.250 0.0015 0.01002 0.00192 -0.0182 0.6056 0.0189 -1.000 0.0292 0.00993 0.00179 -0.0182 0.6035 0.0190 -0.750 0.0570 0.00986 0.00168 -0.0182 0.6016 0.0192 -0.500 0.0848 0.00980 0.00159 -0.0182 0.5992 0.0194 -0.250 0.1126 0.00975 0.00152 -0.0183 0.5966 0.0200 0.000 0.1405 0.00969 0.00147 -0.0184 0.5937 0.0209 0.250 0.1683 0.00964 0.00144 -0.0184 0.5903 0.0235 0.500 0.1959 0.00960 0.00144 -0.0184 0.5859 0.0449 0.750 0.2235 0.00959 0.00145 -0.0185 0.5801 0.0541 1.000 0.2509 0.00951 0.00144 -0.0185 0.5730 0.0834 1.250 0.2709 0.00811 0.00136 -0.0179 0.5680 0.5512 1.500 0.2976 0.00791 0.00140 -0.0177 0.5633 0.6095 1.750 0.3244 0.00780 0.00143 -0.0176 0.5585 0.6477 2.000 0.3490 0.00753 0.00148 -0.0170 0.5537 0.7263 2.250 0.3706 0.00722 0.00166 -0.0153 0.5478 0.8528 2.500 0.3945 0.00719 0.00178 -0.0142 0.5412 0.9039 2.750 0.4203 0.00716 0.00189 -0.0133 0.5288 0.9467 3.000 0.4483 0.00721 0.00176 -0.0134 0.4629 0.9563 3.250 0.4762 0.00753 0.00192 -0.0136 0.4350 0.9629 3.500 0.5062 0.00774 0.00207 -0.0142 0.4050 0.9684 3.750 0.5358 0.00805 0.00222 -0.0149 0.3616 0.9745 4.000 0.5668 0.00835 0.00240 -0.0159 0.3298 0.9794 4.250 0.5970 0.00869 0.00263 -0.0168 0.2932 0.9848 4.500 0.6285 0.00902 0.00284 -0.0180 0.2606 0.9886 4.750 0.6593 0.00946 0.00310 -0.0191 0.2198 0.9927 5.000 0.6900 0.00995 0.00339 -0.0203 0.1767 0.9963 5.250 0.7209 0.01037 0.00370 -0.0214 0.1472 0.9996 5.500 0.7435 0.01072 0.00396 -0.0207 0.1233 1.0000 5.750 0.7649 0.01111 0.00425 -0.0197 0.1020 1.0000 6.000 0.7869 0.01146 0.00455 -0.0189 0.0865 1.0000 6.250 0.8094 0.01182 0.00489 -0.0181 0.0743 1.0000 6.500 0.8322 0.01220 0.00524 -0.0174 0.0621 1.0000 6.750 0.8549 0.01261 0.00561 -0.0167 0.0496 1.0000 7.000 0.8776 0.01307 0.00603 -0.0160 0.0381 1.0000 7.250 0.9002 0.01356 0.00651 -0.0154 0.0292 1.0000 7.500 0.9234 0.01399 0.00699 -0.0148 0.0250 1.0000 7.750 0.9455 0.01458 0.00758 -0.0141 0.0202 1.0000 8.000 0.9689 0.01500 0.00807 -0.0136 0.0183 1.0000 8.250 0.9917 0.01548 0.00859 -0.0130 0.0162 1.0000 8.500 1.0137 0.01606 0.00920 -0.0124 0.0144 1.0000 8.750 1.0350 0.01673 0.00995 -0.0116 0.0132 1.0000 9.000 1.0574 0.01723 0.01056 -0.0110 0.0125 1.0000 9.250 1.0793 0.01779 0.01120 -0.0104 0.0115 1.0000 9.500 1.1006 0.01838 0.01185 -0.0097 0.0103 1.0000 9.750 1.1194 0.01925 0.01277 -0.0087 0.0087 1.0000 10.000 1.1405 0.01981 0.01342 -0.0081 0.0078 1.0000 10.250 1.1605 0.02048 0.01419 -0.0073 0.0068 1.0000 10.500 1.1793 0.02123 0.01502 -0.0064 0.0060 1.0000 10.750 1.1956 0.02221 0.01608 -0.0052 0.0054 1.0000 11.000 1.2116 0.02316 0.01715 -0.0039 0.0050 1.0000 11.250 1.2262 0.02417 0.01829 -0.0026 0.0047 1.0000 11.500 1.2385 0.02523 0.01947 -0.0009 0.0045 1.0000 11.750 1.2484 0.02634 0.02070 0.0010 0.0042 1.0000 12.000 1.2572 0.02754 0.02203 0.0028 0.0040 1.0000 12.250 1.2646 0.02888 0.02349 0.0046 0.0039 1.0000 12.500 1.2702 0.03043 0.02516 0.0062 0.0037 1.0000 12.750 1.2732 0.03228 0.02715 0.0076 0.0036 1.0000 13.000 1.2735 0.03452 0.02954 0.0087 0.0035 1.0000 13.250 1.2707 0.03729 0.03248 0.0093 0.0034 1.0000 13.500 1.2649 0.04068 0.03605 0.0092 0.0033 1.0000 13.750 1.2563 0.04471 0.04030 0.0084 0.0032 1.0000 14.000 1.2507 0.04858 0.04434 0.0073 0.0032 1.0000 14.250 1.2430 0.05290 0.04883 0.0059 0.0032 1.0000 14.500 1.2326 0.05771 0.05381 0.0041 0.0032 1.0000 14.750 1.2199 0.06300 0.05927 0.0019 0.0031 1.0000 15.000 1.2050 0.06898 0.06543 -0.0009 0.0031 1.0000 15.250 1.1884 0.07580 0.07241 -0.0044 0.0031 1.0000 15.500 1.1698 0.08331 0.08008 -0.0084 0.0031 1.0000 15.750 1.1494 0.09154 0.08846 -0.0127 0.0031 1.0000 16.000 1.1278 0.10030 0.09736 -0.0173 0.0032 1.0000 16.250 1.1054 0.10936 0.10655 -0.0219 0.0032 1.0000