XFOIL Version 6.96 Calculated polar for: GOE 593 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5917 0.05168 0.04938 -0.0715 0.9949 0.0220 -10.000 -0.5920 0.04404 0.04142 -0.0799 0.9871 0.0224 -9.250 -0.5446 0.03300 0.02955 -0.0882 0.9735 0.0243 -9.000 -0.5402 0.02808 0.02396 -0.0877 0.9658 0.0251 -8.750 -0.5161 0.02589 0.02125 -0.0885 0.9623 0.0259 -8.500 -0.4912 0.02296 0.01810 -0.0898 0.9603 0.0268 -8.250 -0.4656 0.02245 0.01757 -0.0898 0.9556 0.0276 -8.000 -0.4376 0.02167 0.01671 -0.0902 0.9517 0.0287 -7.750 -0.4069 0.02047 0.01526 -0.0912 0.9493 0.0300 -7.500 -0.3732 0.01965 0.01416 -0.0925 0.9476 0.0309 -7.250 -0.3417 0.01753 0.01192 -0.0941 0.9462 0.0323 -7.000 -0.3167 0.01702 0.01138 -0.0937 0.9403 0.0334 -6.750 -0.2837 0.01636 0.01063 -0.0948 0.9370 0.0348 -6.500 -0.2483 0.01561 0.00975 -0.0964 0.9343 0.0361 -6.250 -0.2124 0.01472 0.00871 -0.0981 0.9320 0.0371 -6.000 -0.1866 0.01376 0.00774 -0.0979 0.9254 0.0387 -5.750 -0.1539 0.01327 0.00722 -0.0989 0.9205 0.0404 -5.500 -0.1175 0.01271 0.00659 -0.1007 0.9167 0.0419 -5.250 -0.0915 0.01236 0.00617 -0.1002 0.9084 0.0432 -5.000 -0.0603 0.01168 0.00542 -0.1009 0.9024 0.0448 -4.750 -0.0348 0.01122 0.00496 -0.1004 0.8940 0.0467 -4.500 -0.0054 0.01088 0.00457 -0.1006 0.8867 0.0486 -4.250 0.0199 0.01062 0.00426 -0.0999 0.8776 0.0506 -4.000 0.0482 0.01029 0.00387 -0.0998 0.8695 0.0531 -3.750 0.0709 0.00998 0.00356 -0.0986 0.8590 0.0568 -3.500 0.0976 0.00977 0.00329 -0.0982 0.8492 0.0609 -3.250 0.1226 0.00948 0.00300 -0.0974 0.8377 0.0697 -3.000 0.1456 0.00921 0.00281 -0.0962 0.8249 0.0937 -2.750 0.1702 0.00903 0.00269 -0.0954 0.8131 0.1205 -2.500 0.1961 0.00892 0.00257 -0.0948 0.8029 0.1377 -2.250 0.2211 0.00881 0.00244 -0.0941 0.7917 0.1529 -2.000 0.2457 0.00869 0.00234 -0.0933 0.7806 0.1711 -1.750 0.2703 0.00853 0.00225 -0.0925 0.7699 0.2026 -1.500 0.2939 0.00832 0.00218 -0.0916 0.7590 0.2623 -1.250 0.3162 0.00805 0.00212 -0.0905 0.7477 0.3368 -1.000 0.3337 0.00749 0.00210 -0.0885 0.7370 0.5195 -0.750 0.3471 0.00691 0.00213 -0.0852 0.7266 0.7110 -0.500 0.3705 0.00656 0.00228 -0.0836 0.7163 0.8738 -0.250 0.4229 0.00667 0.00238 -0.0886 0.7060 0.9310 0.000 0.4656 0.00681 0.00243 -0.0915 0.6953 0.9524 0.250 0.5080 0.00696 0.00251 -0.0945 0.6845 0.9665 0.500 0.5515 0.00711 0.00257 -0.0977 0.6739 0.9760 1.000 0.6382 0.00738 0.00267 -0.1042 0.6490 0.9914 1.250 0.6882 0.00747 0.00268 -0.1090 0.6357 0.9982 1.500 0.7179 0.00753 0.00268 -0.1095 0.6232 1.0000 1.750 0.7372 0.00761 0.00269 -0.1078 0.6108 1.0000 2.000 0.7563 0.00770 0.00271 -0.1059 0.5973 1.0000 2.250 0.7751 0.00780 0.00274 -0.1040 0.5823 1.0000 2.500 0.7938 0.00791 0.00279 -0.1021 0.5657 1.0000 2.750 0.8123 0.00804 0.00285 -0.1001 0.5477 1.0000 3.000 0.8304 0.00819 0.00292 -0.0981 0.5280 1.0000 3.250 0.8475 0.00838 0.00302 -0.0958 0.5064 1.0000 3.500 0.8644 0.00859 0.00313 -0.0936 0.4842 1.0000 3.750 0.8810 0.00884 0.00327 -0.0913 0.4612 1.0000 4.000 0.8973 0.00911 0.00342 -0.0889 0.4399 1.0000 4.250 0.9145 0.00938 0.00360 -0.0867 0.4195 1.0000 4.500 0.9317 0.00965 0.00378 -0.0846 0.4013 1.0000 4.750 0.9492 0.00992 0.00398 -0.0825 0.3850 1.0000 5.000 0.9671 0.01019 0.00418 -0.0805 0.3705 1.0000 5.250 0.9849 0.01046 0.00439 -0.0785 0.3566 1.0000 5.500 1.0026 0.01074 0.00461 -0.0765 0.3436 1.0000 5.750 1.0205 0.01102 0.00483 -0.0746 0.3322 1.0000 6.000 1.0397 0.01125 0.00504 -0.0729 0.3223 1.0000 6.250 1.0572 0.01154 0.00530 -0.0709 0.3139 1.0000 6.500 1.0763 0.01176 0.00552 -0.0692 0.3051 1.0000 6.750 1.0928 0.01204 0.00577 -0.0670 0.2971 1.0000 7.000 1.1103 0.01226 0.00601 -0.0650 0.2891 1.0000 7.250 1.1267 0.01255 0.00627 -0.0629 0.2821 1.0000 7.500 1.1446 0.01278 0.00651 -0.0610 0.2737 1.0000 7.750 1.1614 0.01307 0.00679 -0.0590 0.2664 1.0000 8.000 1.1799 0.01332 0.00707 -0.0574 0.2590 1.0000 8.250 1.1964 0.01366 0.00739 -0.0554 0.2527 1.0000 8.500 1.2158 0.01389 0.00768 -0.0539 0.2461 1.0000 9.000 1.2511 0.01453 0.00835 -0.0505 0.2307 1.0000 9.250 1.2672 0.01492 0.00872 -0.0487 0.2215 1.0000 9.500 1.2832 0.01533 0.00911 -0.0468 0.2096 1.0000 9.750 1.2983 0.01580 0.00955 -0.0449 0.1944 1.0000 10.000 1.3123 0.01635 0.01005 -0.0429 0.1729 1.0000 10.250 1.3184 0.01734 0.01082 -0.0399 0.1372 1.0000 10.500 1.3180 0.01875 0.01197 -0.0362 0.1006 1.0000 10.750 1.3230 0.01992 0.01304 -0.0333 0.0832 1.0000 11.000 1.3311 0.02093 0.01403 -0.0309 0.0747 1.0000 11.250 1.3394 0.02197 0.01507 -0.0287 0.0690 1.0000 11.500 1.3489 0.02296 0.01610 -0.0267 0.0648 1.0000 11.750 1.3586 0.02397 0.01716 -0.0249 0.0613 1.0000 12.000 1.3651 0.02521 0.01842 -0.0229 0.0579 1.0000 12.250 1.3734 0.02638 0.01966 -0.0212 0.0550 1.0000 12.500 1.3837 0.02746 0.02082 -0.0198 0.0524 1.0000 12.750 1.3903 0.02884 0.02223 -0.0182 0.0497 1.0000 13.000 1.3914 0.03070 0.02414 -0.0164 0.0470 1.0000 13.250 1.4032 0.03178 0.02531 -0.0154 0.0446 1.0000 13.500 1.4095 0.03334 0.02692 -0.0143 0.0420 1.0000 13.750 1.4087 0.03558 0.02919 -0.0129 0.0392 1.0000 14.000 1.4185 0.03694 0.03066 -0.0122 0.0367 1.0000 14.250 1.4215 0.03899 0.03274 -0.0113 0.0342 1.0000 14.500 1.4212 0.04143 0.03525 -0.0105 0.0319 1.0000 14.750 1.4243 0.04362 0.03752 -0.0099 0.0299 1.0000 15.000 1.4226 0.04640 0.04035 -0.0095 0.0282 1.0000 15.250 1.4163 0.04978 0.04380 -0.0092 0.0269 1.0000 15.500 1.4169 0.05250 0.04663 -0.0091 0.0255 1.0000 15.750 1.4143 0.05566 0.04989 -0.0091 0.0245 1.0000 16.000 1.4102 0.05912 0.05342 -0.0094 0.0235 1.0000 16.250 1.3994 0.06351 0.05789 -0.0100 0.0228 1.0000 16.500 1.3897 0.06789 0.06238 -0.0107 0.0221 1.0000 16.750 1.3836 0.07193 0.06654 -0.0115 0.0214 1.0000 17.000 1.3784 0.07590 0.07062 -0.0124 0.0207 1.0000 17.250 1.3700 0.08039 0.07521 -0.0135 0.0202 1.0000 17.500 1.3616 0.08496 0.07988 -0.0148 0.0198 1.0000 17.750 1.3518 0.08980 0.08481 -0.0162 0.0195 1.0000 18.000 1.3400 0.09496 0.09004 -0.0178 0.0190 1.0000