XFOIL Version 6.96 Calculated polar for: GOE 623 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 ------ -------- --------- --------- -------- -------- -------- -15.250 -1.1036 0.03693 0.03401 -0.0843 1.0000 0.0076 -15.000 -1.1192 0.03323 0.03013 -0.0847 1.0000 0.0076 -14.750 -1.1193 0.03096 0.02770 -0.0838 1.0000 0.0077 -14.500 -1.1125 0.02914 0.02574 -0.0829 1.0000 0.0078 -14.250 -1.1037 0.02750 0.02396 -0.0818 1.0000 0.0079 -14.000 -1.0937 0.02597 0.02232 -0.0805 1.0000 0.0081 -13.750 -1.0819 0.02471 0.02095 -0.0791 1.0000 0.0084 -13.500 -1.0688 0.02362 0.01978 -0.0775 1.0000 0.0086 -13.250 -1.0501 0.02260 0.01866 -0.0769 0.9991 0.0089 -13.000 -1.0232 0.02156 0.01753 -0.0779 0.9965 0.0092 -12.500 -0.9683 0.01976 0.01552 -0.0796 0.9903 0.0099 -12.250 -0.9398 0.01897 0.01463 -0.0805 0.9859 0.0102 -12.000 -0.9117 0.01818 0.01376 -0.0812 0.9789 0.0107 -11.750 -0.8821 0.01752 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0.00192 -0.0772 0.4124 0.9106 2.750 0.7009 0.00705 0.00203 -0.0770 0.3885 0.9622 3.000 0.7347 0.00734 0.00217 -0.0784 0.3577 0.9877 3.250 0.7673 0.00762 0.00232 -0.0797 0.3326 1.0000 3.500 0.7928 0.00786 0.00246 -0.0793 0.3140 1.0000 3.750 0.8185 0.00809 0.00261 -0.0790 0.2977 1.0000 4.000 0.8443 0.00831 0.00276 -0.0787 0.2831 1.0000 4.250 0.8703 0.00853 0.00291 -0.0784 0.2696 1.0000 4.500 0.8962 0.00876 0.00307 -0.0782 0.2573 1.0000 4.750 0.9221 0.00899 0.00325 -0.0779 0.2455 1.0000 5.000 0.9479 0.00922 0.00342 -0.0776 0.2340 1.0000 5.250 0.9739 0.00943 0.00360 -0.0774 0.2241 1.0000 5.500 0.9996 0.00967 0.00379 -0.0771 0.2153 1.0000 5.750 1.0257 0.00987 0.00397 -0.0769 0.2084 1.0000 6.000 1.0513 0.01010 0.00417 -0.0766 0.2015 1.0000 6.250 1.0771 0.01032 0.00438 -0.0764 0.1942 1.0000 6.500 1.1022 0.01058 0.00460 -0.0760 0.1870 1.0000 6.750 1.1276 0.01082 0.00482 -0.0758 0.1798 1.0000 7.000 1.1523 0.01111 0.00507 -0.0754 0.1716 1.0000 7.250 1.1773 0.01136 0.00531 -0.0750 0.1651 1.0000 7.500 1.2016 0.01166 0.00558 -0.0746 0.1583 1.0000 7.750 1.2265 0.01189 0.00582 -0.0742 0.1531 1.0000 8.000 1.2501 0.01223 0.00612 -0.0737 0.1453 1.0000 8.250 1.2743 0.01250 0.00639 -0.0732 0.1389 1.0000 8.500 1.2968 0.01288 0.00672 -0.0726 0.1289 1.0000 8.750 1.3181 0.01334 0.00710 -0.0717 0.1146 1.0000 9.000 1.3271 0.01464 0.00807 -0.0690 0.0652 1.0000 9.250 1.3427 0.01542 0.00877 -0.0673 0.0488 1.0000 9.500 1.3602 0.01602 0.00934 -0.0658 0.0405 1.0000 9.750 1.3761 0.01664 0.00993 -0.0641 0.0322 1.0000 10.000 1.3884 0.01737 0.01060 -0.0618 0.0227 1.0000 10.250 1.4015 0.01808 0.01129 -0.0597 0.0171 1.0000 10.500 1.4162 0.01872 0.01195 -0.0580 0.0149 1.0000 10.750 1.4310 0.01938 0.01263 -0.0564 0.0133 1.0000 11.000 1.4460 0.02004 0.01333 -0.0549 0.0124 1.0000 11.250 1.4597 0.02080 0.01412 -0.0533 0.0114 1.0000 11.500 1.4725 0.02165 0.01501 -0.0517 0.0105 1.0000 11.750 1.4865 0.02244 0.01586 -0.0503 0.0101 1.0000 12.000 1.4995 0.02333 0.01679 -0.0489 0.0095 1.0000 12.250 1.5114 0.02433 0.01784 -0.0476 0.0090 1.0000 12.500 1.5221 0.02544 0.01899 -0.0462 0.0085 1.0000 12.750 1.5315 0.02671 0.02031 -0.0448 0.0080 1.0000 13.000 1.5420 0.02791 0.02158 -0.0436 0.0078 1.0000 13.250 1.5518 0.02921 0.02295 -0.0425 0.0076 1.0000 13.500 1.5607 0.03063 0.02443 -0.0414 0.0073 1.0000 13.750 1.5684 0.03218 0.02604 -0.0404 0.0070 1.0000 14.000 1.5751 0.03387 0.02780 -0.0394 0.0068 1.0000 14.250 1.5806 0.03572 0.02972 -0.0386 0.0066 1.0000 14.500 1.5846 0.03777 0.03184 -0.0377 0.0064 1.0000 14.750 1.5868 0.04007 0.03421 -0.0370 0.0062 1.0000 15.000 1.5869 0.04266 0.03690 -0.0364 0.0060 1.0000 15.250 1.5891 0.04513 0.03945 -0.0360 0.0059 1.0000 15.500 1.5906 0.04774 0.04214 -0.0358 0.0057 1.0000 15.750 1.5908 0.05059 0.04508 -0.0357 0.0056 1.0000 16.000 1.5899 0.05366 0.04825 -0.0357 0.0055 1.0000 16.250 1.5883 0.05689 0.05156 -0.0359 0.0054 1.0000 16.500 1.5851 0.06034 0.05511 -0.0362 0.0053 1.0000 16.750 1.5804 0.06409 0.05896 -0.0366 0.0052 1.0000 17.000 1.5744 0.06810 0.06307 -0.0373 0.0051 1.0000 17.250 1.5671 0.07234 0.06740 -0.0380 0.0050 1.0000 17.500 1.5583 0.07683 0.07200 -0.0389 0.0049 1.0000 17.750 1.5481 0.08165 0.07692 -0.0400 0.0049 1.0000 18.000 1.5365 0.08681 0.08219 -0.0413 0.0048 1.0000 18.250 1.5239 0.09217 0.08767 -0.0428 0.0047 1.0000 18.500 1.5098 0.09788 0.09349 -0.0446 0.0047 1.0000 18.750 1.4946 0.10390 0.09963 -0.0466 0.0047 1.0000 19.000 1.4792 0.11007 0.10591 -0.0487 0.0046 1.0000 19.250 1.4627 0.11647 0.11243 -0.0511 0.0046 1.0000