XFOIL Version 6.96 Calculated polar for: GOE 738 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.9581 0.06972 0.06471 -0.0356 1.0000 0.0408 -15.000 -0.9817 0.06285 0.05763 -0.0402 1.0000 0.0409 -14.750 -0.9965 0.05778 0.05240 -0.0432 1.0000 0.0411 -14.500 -1.0075 0.05359 0.04806 -0.0452 1.0000 0.0413 -14.250 -1.0157 0.05006 0.04438 -0.0465 1.0000 0.0416 -14.000 -1.0217 0.04703 0.04122 -0.0471 1.0000 0.0419 -13.750 -1.0258 0.04442 0.03847 -0.0471 1.0000 0.0423 -13.500 -1.0285 0.04213 0.03604 -0.0466 1.0000 0.0428 -13.250 -1.0299 0.04003 0.03378 -0.0457 1.0000 0.0432 -13.000 -1.0299 0.03814 0.03173 -0.0444 1.0000 0.0437 -12.750 -1.0284 0.03643 0.02984 -0.0428 1.0000 0.0443 -12.500 -1.0248 0.03486 0.02809 -0.0410 1.0000 0.0448 -12.250 -1.0192 0.03346 0.02652 -0.0391 1.0000 0.0453 -12.000 -1.0074 0.03227 0.02532 -0.0376 1.0000 0.0457 -11.750 -0.9950 0.03125 0.02429 -0.0361 1.0000 0.0462 -11.500 -0.9721 0.03024 0.02317 -0.0366 0.9048 0.0469 -11.000 -0.9420 0.02868 0.02128 -0.0335 0.8521 0.0483 -10.500 -0.9099 0.02709 0.01936 -0.0304 0.8240 0.0502 -10.250 -0.8928 0.02633 0.01841 -0.0288 0.8130 0.0512 -10.000 -0.8753 0.02555 0.01756 -0.0274 0.8029 0.0520 -9.750 -0.8566 0.02486 0.01684 -0.0262 0.7935 0.0529 -9.500 -0.8376 0.02424 0.01613 -0.0249 0.7849 0.0538 -9.250 -0.8172 0.02360 0.01542 -0.0238 0.7764 0.0550 -9.000 -0.7966 0.02298 0.01468 -0.0227 0.7684 0.0563 -8.750 -0.7751 0.02242 0.01399 -0.0216 0.7609 0.0577 -8.500 -0.7545 0.02178 0.01332 -0.0205 0.7531 0.0591 -8.250 -0.7334 0.02127 0.01275 -0.0194 0.7465 0.0607 -8.000 -0.7109 0.02075 0.01219 -0.0186 0.7388 0.0625 -7.750 -0.6885 0.02027 0.01160 -0.0176 0.7320 0.0644 -7.500 -0.6659 0.01977 0.01103 -0.0167 0.7254 0.0662 -7.250 -0.6437 0.01923 0.01049 -0.0158 0.7181 0.0683 -7.000 -0.6207 0.01882 0.01001 -0.0149 0.7119 0.0709 -6.750 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-2.000 -0.1212 0.01293 0.00446 -0.0025 0.5881 0.3260 -1.750 -0.0975 0.01263 0.00432 -0.0016 0.5831 0.3745 -1.500 -0.0744 0.01229 0.00425 -0.0007 0.5777 0.4366 -1.250 -0.0517 0.01197 0.00422 0.0005 0.5719 0.5042 -1.000 -0.0286 0.01172 0.00418 0.0017 0.5666 0.5668 -0.750 -0.0044 0.01155 0.00417 0.0027 0.5613 0.6182 -0.500 0.0210 0.01142 0.00419 0.0036 0.5547 0.6597 -0.250 0.0469 0.01135 0.00418 0.0043 0.5489 0.6957 0.000 0.0736 0.01130 0.00420 0.0049 0.5428 0.7286 0.250 0.1009 0.01125 0.00423 0.0054 0.5351 0.7593 0.500 0.1286 0.01125 0.00421 0.0059 0.5286 0.7873 0.750 0.1579 0.01125 0.00427 0.0059 0.5210 0.8112 1.000 0.1888 0.01127 0.00429 0.0057 0.5136 0.8327 1.250 0.2225 0.01133 0.00436 0.0049 0.5061 0.8550 1.500 0.2611 0.01143 0.00449 0.0032 0.4988 0.8828 1.750 0.3027 0.01159 0.00461 0.0008 0.4931 0.9056 2.000 0.3421 0.01174 0.00478 -0.0011 0.4862 0.9218 2.250 0.3840 0.01189 0.00489 -0.0037 0.4791 0.9320 2.500 0.4197 0.01203 0.00498 -0.0051 0.4727 0.9413 2.750 0.4559 0.01216 0.00510 -0.0067 0.4653 0.9489 3.000 0.4900 0.01229 0.00518 -0.0078 0.4590 0.9564 3.250 0.5260 0.01241 0.00530 -0.0095 0.4521 0.9627 3.500 0.5596 0.01253 0.00540 -0.0106 0.4448 0.9697 3.750 0.5958 0.01265 0.00548 -0.0123 0.4379 0.9751 4.000 0.6295 0.01278 0.00562 -0.0136 0.4299 0.9816 4.250 0.6663 0.01289 0.00568 -0.0155 0.4221 0.9862 4.500 0.7017 0.01301 0.00582 -0.0171 0.4126 0.9914 4.750 0.7380 0.01313 0.00590 -0.0190 0.4033 0.9960 5.000 0.7740 0.01325 0.00603 -0.0209 0.3925 1.0000 5.250 0.7953 0.01340 0.00617 -0.0198 0.3826 1.0000 5.500 0.8161 0.01359 0.00631 -0.0187 0.3713 1.0000 5.750 0.8373 0.01379 0.00650 -0.0176 0.3583 1.0000 6.000 0.8581 0.01403 0.00670 -0.0164 0.3448 1.0000 6.250 0.8784 0.01430 0.00692 -0.0153 0.3299 1.0000 6.500 0.8982 0.01463 0.00718 -0.0140 0.3148 1.0000 6.750 0.9176 0.01499 0.00748 -0.0128 0.3007 1.0000 7.000 0.9365 0.01539 0.00781 -0.0114 0.2887 1.0000 7.250 0.9557 0.01577 0.00816 -0.0101 0.2782 1.0000 7.500 0.9740 0.01620 0.00855 -0.0088 0.2679 1.0000 7.750 0.9917 0.01666 0.00897 -0.0073 0.2589 1.0000 8.000 1.0098 0.01708 0.00939 -0.0059 0.2517 1.0000 8.250 1.0275 0.01753 0.00983 -0.0044 0.2450 1.0000 8.500 1.0433 0.01804 0.01032 -0.0028 0.2383 1.0000 8.750 1.0602 0.01849 0.01079 -0.0012 0.2310 1.0000 9.000 1.0741 0.01905 0.01133 0.0006 0.2244 1.0000 9.250 1.0892 0.01954 0.01186 0.0023 0.2185 1.0000 9.500 1.1027 0.02008 0.01242 0.0042 0.2121 1.0000 9.750 1.1117 0.02078 0.01309 0.0066 0.2060 1.0000 10.000 1.1220 0.02129 0.01368 0.0090 0.1999 1.0000 10.250 1.1269 0.02202 0.01443 0.0117 0.1936 1.0000 10.500 1.1333 0.02287 0.01531 0.0138 0.1874 1.0000 10.750 1.1416 0.02377 0.01626 0.0155 0.1795 1.0000 11.000 1.1489 0.02483 0.01734 0.0170 0.1713 1.0000 11.250 1.1548 0.02608 0.01859 0.0183 0.1617 1.0000 11.500 1.1608 0.02741 0.01993 0.0194 0.1510 1.0000 11.750 1.1644 0.02900 0.02150 0.0205 0.1414 1.0000 12.000 1.1658 0.03085 0.02332 0.0214 0.1328 1.0000 12.250 1.1674 0.03276 0.02522 0.0222 0.1251 1.0000 12.500 1.1687 0.03478 0.02724 0.0229 0.1188 1.0000 12.750 1.1695 0.03689 0.02937 0.0234 0.1130 1.0000 13.000 1.1692 0.03918 0.03168 0.0238 0.1082 1.0000 13.250 1.1714 0.04130 0.03385 0.0242 0.1033 1.0000 13.500 1.1707 0.04374 0.03632 0.0243 0.0994 1.0000 13.750 1.1708 0.04617 0.03879 0.0245 0.0961 1.0000 14.000 1.1727 0.04849 0.04118 0.0245 0.0925 1.0000 14.250 1.1736 0.05101 0.04375 0.0244 0.0899 1.0000 14.500 1.1725 0.05381 0.04658 0.0241 0.0876 1.0000 14.750 1.1739 0.05639 0.04921 0.0239 0.0855 1.0000 15.000 1.1764 0.05890 0.05181 0.0236 0.0835 1.0000 15.250 1.1780 0.06155 0.05452 0.0232 0.0817 1.0000 15.500 1.1789 0.06434 0.05736 0.0227 0.0802 1.0000 15.750 1.1793 0.06719 0.06024 0.0222 0.0788 1.0000 16.000 1.1790 0.07015 0.06323 0.0216 0.0774 1.0000 16.250 1.1819 0.07277 0.06592 0.0211 0.0762 1.0000 16.500 1.1844 0.07548 0.06871 0.0206 0.0749 1.0000 16.750 1.1864 0.07828 0.07159 0.0199 0.0736 1.0000 17.000 1.1874 0.08126 0.07464 0.0191 0.0722 1.0000 17.250 1.1882 0.08429 0.07772 0.0183 0.0710 1.0000 17.500 1.1892 0.08727 0.08072 0.0175 0.0698 1.0000 17.750 1.1914 0.08998 0.08342 0.0168 0.0686 1.0000 18.000 1.1911 0.09334 0.08690 0.0157 0.0674 1.0000 18.250 1.1908 0.09669 0.09037 0.0145 0.0660 1.0000 18.500 1.1901 0.10014 0.09390 0.0132 0.0648 1.0000 18.750 1.1884 0.10377 0.09760 0.0118 0.0634 1.0000