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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4407 0.08222 0.08078 -0.0190 1.0000 0.0085 -9.250 -0.4455 0.07689 0.07546 -0.0213 1.0000 0.0085 -9.000 -0.4523 0.07090 0.06948 -0.0247 1.0000 0.0085 -8.750 -0.4655 0.06378 0.06235 -0.0308 1.0000 0.0085 -8.500 -0.4818 0.05859 0.05711 -0.0344 1.0000 0.0085 -8.250 -0.4930 0.05356 0.05198 -0.0368 0.9716 0.0085 -8.000 -0.4995 0.04905 0.04734 -0.0369 0.9512 0.0085 -7.750 -0.5031 0.04470 0.04283 -0.0362 0.9293 0.0085 -7.500 -0.5041 0.04038 0.03830 -0.0350 0.8976 0.0085 -7.250 -0.5042 0.03685 0.03420 -0.0329 0.7667 0.0085 -6.750 -0.5339 0.03856 0.03523 -0.0293 0.7654 0.0088 -6.500 -0.5191 0.03632 0.03264 -0.0287 0.7082 0.0090 -5.750 -0.4618 0.02971 0.02535 -0.0270 0.6608 0.0099 -5.500 -0.4399 0.02729 0.02268 -0.0261 0.6539 0.0108 -5.250 -0.3943 0.01163 0.00685 -0.0250 0.6427 0.0122 -5.000 -0.3739 0.00976 0.00465 -0.0239 0.6397 0.0123 -4.500 -0.3457 0.01692 0.01111 -0.0220 0.6376 0.0136 -4.250 -0.3197 0.01596 0.01005 -0.0218 0.6350 0.0144 -4.000 -0.2928 0.01543 0.00941 -0.0216 0.6326 0.0161 -3.750 -0.2670 0.01385 0.00761 -0.0211 0.6305 0.0184 -3.500 -0.2407 0.01303 0.00676 -0.0209 0.6284 0.0200 -3.250 -0.2140 0.01233 0.00600 -0.0206 0.6265 0.0218 -3.000 -0.1880 0.01104 0.00455 -0.0195 0.6250 0.0162 -2.750 -0.1620 0.01044 0.00389 -0.0191 0.6235 0.0163 -2.500 -0.1356 0.00999 0.00340 -0.0188 0.6214 0.0166 -2.250 -0.1083 0.00975 0.00313 -0.0187 0.6191 0.0172 -2.000 -0.0818 0.00933 0.00264 -0.0185 0.6171 0.0171 -1.750 -0.0552 0.00890 0.00213 -0.0182 0.6155 0.0176 -1.500 -0.0278 0.00868 0.00184 -0.0181 0.6137 0.0183 -1.250 -0.0001 0.00854 0.00166 -0.0181 0.6115 0.0189 -1.000 0.0279 0.00842 0.00152 -0.0182 0.6099 0.0198 -0.750 0.0560 0.00832 0.00140 -0.0182 0.6079 0.0207 -0.500 0.0841 0.00825 0.00131 -0.0183 0.6055 0.0216 -0.250 0.1119 0.00813 0.00125 -0.0184 0.6025 0.0396 0.000 0.1396 0.00812 0.00122 -0.0184 0.5979 0.0514 0.250 0.1677 0.00805 0.00120 -0.0185 0.5933 0.0599 0.500 0.1902 0.00688 0.00104 -0.0181 0.5889 0.4292 0.750 0.2148 0.00640 0.00107 -0.0178 0.5854 0.5837 1.000 0.2406 0.00614 0.00108 -0.0176 0.5821 0.6659 1.250 0.2651 0.00576 0.00111 -0.0169 0.5788 0.7707 1.500 0.2896 0.00558 0.00120 -0.0160 0.5754 0.8533 1.750 0.3143 0.00557 0.00129 -0.0152 0.5712 0.8970 2.000 0.3384 0.00558 0.00139 -0.0141 0.5672 0.9273 2.250 0.3648 0.00558 0.00143 -0.0137 0.5630 0.9398 2.500 0.3913 0.00564 0.00147 -0.0133 0.5549 0.9486 2.750 0.4187 0.00561 0.00149 -0.0132 0.5450 0.9570 3.000 0.4471 0.00562 0.00152 -0.0132 0.5362 0.9647 3.250 0.4766 0.00560 0.00152 -0.0136 0.5137 0.9716 3.500 0.5059 0.00593 0.00155 -0.0141 0.4479 0.9800 3.750 0.5391 0.00613 0.00171 -0.0154 0.4281 0.9850 4.000 0.5719 0.00638 0.00184 -0.0168 0.3882 0.9873 4.250 0.6044 0.00673 0.00201 -0.0181 0.3434 0.9898 4.500 0.6360 0.00715 0.00222 -0.0194 0.2926 0.9929 4.750 0.6682 0.00758 0.00245 -0.0208 0.2422 0.9951 5.000 0.7009 0.00799 0.00268 -0.0223 0.2028 0.9970 5.250 0.7334 0.00834 0.00291 -0.0238 0.1723 0.9989 5.500 0.7618 0.00867 0.00315 -0.0243 0.1487 1.0000 5.750 0.7829 0.00897 0.00337 -0.0232 0.1275 1.0000 6.000 0.8036 0.00930 0.00361 -0.0221 0.1065 1.0000 6.250 0.8249 0.00965 0.00388 -0.0210 0.0890 1.0000 6.500 0.8464 0.01001 0.00418 -0.0200 0.0735 1.0000 6.750 0.8684 0.01040 0.00450 -0.0191 0.0578 1.0000 7.000 0.8904 0.01085 0.00487 -0.0183 0.0410 1.0000 7.250 0.9120 0.01142 0.00535 -0.0174 0.0270 1.0000 7.500 0.9357 0.01180 0.00575 -0.0169 0.0230 1.0000 7.750 0.9579 0.01241 0.00638 -0.0161 0.0188 1.0000 8.000 0.9823 0.01272 0.00674 -0.0157 0.0177 1.0000 8.250 1.0065 0.01308 0.00713 -0.0153 0.0163 1.0000 8.500 1.0296 0.01357 0.00763 -0.0148 0.0146 1.0000 8.750 1.0506 0.01432 0.00848 -0.0139 0.0127 1.0000 9.000 1.0748 0.01466 0.00886 -0.0136 0.0119 1.0000 9.250 1.0981 0.01510 0.00933 -0.0131 0.0106 1.0000 9.500 1.1154 0.01625 0.01057 -0.0118 0.0087 1.0000 9.750 1.1389 0.01662 0.01099 -0.0114 0.0081 1.0000 10.000 1.1607 0.01719 0.01161 -0.0107 0.0074 1.0000 10.250 1.1820 0.01778 0.01226 -0.0101 0.0068 1.0000 10.500 1.2000 0.01871 0.01326 -0.0090 0.0061 1.0000 10.750 1.2121 0.02020 0.01491 -0.0071 0.0056 1.0000 11.000 1.2317 0.02084 0.01564 -0.0063 0.0054 1.0000 11.250 1.2493 0.02164 0.01653 -0.0052 0.0051 1.0000 11.500 1.2649 0.02258 0.01757 -0.0039 0.0049 1.0000 11.750 1.2781 0.02364 0.01873 -0.0023 0.0047 1.0000 12.000 1.2880 0.02471 0.01991 -0.0003 0.0045 1.0000 12.250 1.2960 0.02590 0.02122 0.0018 0.0044 1.0000 12.500 1.3027 0.02722 0.02264 0.0037 0.0043 1.0000 12.750 1.3076 0.02874 0.02428 0.0055 0.0042 1.0000 13.000 1.3103 0.03053 0.02620 0.0071 0.0041 1.0000 13.250 1.3107 0.03268 0.02848 0.0084 0.0040 1.0000 13.500 1.3082 0.03532 0.03128 0.0092 0.0040 1.0000 13.750 1.3035 0.03850 0.03461 0.0093 0.0039 1.0000 14.000 1.2961 0.04229 0.03857 0.0087 0.0039 1.0000 14.250 1.2862 0.04666 0.04312 0.0076 0.0038 1.0000 14.500 1.2745 0.05146 0.04809 0.0060 0.0038 1.0000 14.750 1.2610 0.05666 0.05345 0.0041 0.0038 1.0000 15.000 1.2452 0.06231 0.05926 0.0019 0.0038 1.0000 15.250 1.2275 0.06867 0.06578 -0.0010 0.0037 1.0000 15.500 1.2114 0.07536 0.07262 -0.0045 0.0038 1.0000 15.750 1.1942 0.08260 0.08000 -0.0083 0.0038 1.0000 16.000 1.1761 0.09034 0.08787 -0.0124 0.0038 1.0000 16.250 1.1591 0.09811 0.09577 -0.0165 0.0038 1.0000 16.500 1.1399 0.10646 0.10423 -0.0209 0.0038 1.0000 16.750 1.1201 0.11504 0.11292 -0.0252 0.0039 1.0000 17.000 1.0993 0.12404 0.12203 -0.0298 0.0039 1.0000 17.250 1.0765 0.13371 0.13181 -0.0347 0.0040 1.0000 17.500 1.0453 0.14592 0.14417 -0.0409 0.0041 1.0000