XFOIL Version 6.94 Calculated polar for: GOE 493 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4018 0.00999 0.00412 -0.0970 0.7505 0.6704 0.500 0.4531 0.00990 0.00410 -0.0958 0.7348 0.7101 1.000 0.5057 0.00980 0.00406 -0.0947 0.7186 0.7550 1.500 0.5515 0.00973 0.00414 -0.0923 0.7028 0.8048 2.000 0.6011 0.00969 0.00427 -0.0907 0.6883 0.8640 2.500 0.6799 0.00980 0.00446 -0.0953 0.6738 0.9276 3.000 0.7731 0.00999 0.00468 -0.1033 0.6552 0.9686 3.500 0.8456 0.01016 0.00458 -0.1070 0.6046 1.0000 4.000 0.8624 0.01041 0.00461 -0.0992 0.5628 1.0000 4.500 0.8836 0.01081 0.00481 -0.0923 0.5188 1.0000 5.000 0.9034 0.01132 0.00511 -0.0851 0.4744 1.0000 5.500 0.9148 0.01197 0.00552 -0.0764 0.4213 1.0000 6.000 0.9027 0.01362 0.00651 -0.0642 0.3164 1.0000 6.500 0.9195 0.01489 0.00749 -0.0578 0.2577 1.0000 7.000 0.9119 0.01752 0.00937 -0.0485 0.1267 1.0000 7.500 0.9151 0.02002 0.01139 -0.0416 0.0412 1.0000 8.000 0.9375 0.02167 0.01296 -0.0376 0.0260 1.0000 8.500 0.9665 0.02304 0.01438 -0.0346 0.0211 1.0000 9.000 0.9957 0.02448 0.01588 -0.0318 0.0178 1.0000 9.500 1.0150 0.02663 0.01801 -0.0283 0.0042 1.0000 10.000 1.0382 0.02865 0.02017 -0.0254 0.0039 1.0000 10.500 1.0596 0.03092 0.02258 -0.0227 0.0038 1.0000 11.000 1.0789 0.03347 0.02529 -0.0201 0.0038 1.0000 11.500 1.0958 0.03637 0.02836 -0.0177 0.0037 1.0000 12.000 1.1109 0.03957 0.03175 -0.0156 0.0037 1.0000 12.500 1.1241 0.04313 0.03549 -0.0137 0.0038 1.0000 13.000 1.1353 0.04703 0.03960 -0.0121 0.0038 1.0000 13.500 1.1439 0.05141 0.04418 -0.0108 0.0039 1.0000 14.000 1.1500 0.05623 0.04922 -0.0098 0.0039 1.0000 14.500 1.1530 0.06164 0.05485 -0.0093 0.0040 1.0000 15.000 1.1525 0.06767 0.06111 -0.0092 0.0040 1.0000 15.500 1.1489 0.07435 0.06801 -0.0096 0.0041 1.0000 16.000 1.1412 0.08188 0.07575 -0.0106 0.0042 1.0000 16.500 1.1336 0.08960 0.08369 -0.0121 0.0042 1.0000 17.000 1.1260 0.09760 0.09189 -0.0140 0.0043 1.0000 17.500 1.1223 0.10532 0.09982 -0.0163 0.0043 1.0000 18.000 1.1193 0.11318 0.10790 -0.0190 0.0045 1.0000 18.500 1.1136 0.12163 0.11660 -0.0222 0.0046 1.0000 19.000 1.1069 0.13043 0.12565 -0.0259 0.0047 1.0000 19.500 1.0980 0.13988 0.13538 -0.0303 0.0048 1.0000 20.000 1.0861 0.15026 0.14603 -0.0357 0.0050 1.0000 20.500 1.0697 0.16213 0.15820 -0.0424 0.0051 1.0000 21.000 1.0495 0.17565 0.17201 -0.0504 0.0052 1.0000 21.500 1.0240 0.19185 0.18850 -0.0603 0.0052 1.0000 23.500 0.7610 0.28097 0.27871 -0.1102 0.0163 1.0000 24.000 0.7704 0.28858 0.28634 -0.1136 0.0156 1.0000 25.000 0.7846 0.30706 0.30486 -0.1213 0.0145 1.0000 25.500 0.7924 0.31567 0.31349 -0.1249 0.0135 1.0000 26.000 0.8007 0.32346 0.32131 -0.1282 0.0127 1.0000 26.500 0.8110 0.33103 0.32890 -0.1308 0.0124 1.0000 27.000 0.8141 0.34187 0.33976 -0.1355 0.0117 1.0000 27.500 0.8209 0.35068 0.34859 -0.1390 0.0108 1.0000 28.000 0.8279 0.35870 0.35663 -0.1423 0.0103 1.0000 28.500 0.8356 0.36625 0.36422 -0.1451 0.0099 1.0000 29.000 0.8399 0.37646 0.37445 -0.1491 0.0097 1.0000 29.500 0.8453 0.38605 0.38406 -0.1526 0.0091 1.0000 30.000 0.8507 0.39473 0.39277 -0.1559 0.0086 1.0000 30.500 0.8558 0.40310 0.40116 -0.1591 0.0082 1.0000 31.000 0.8609 0.41084 0.40894 -0.1622 0.0078 1.0000 31.500 0.8656 0.41940 0.41751 -0.1651 0.0077 1.0000 32.000 0.8688 0.42876 0.42691 -0.1687 0.0077 1.0000 32.500 0.8724 0.43802 0.43619 -0.1720 0.0075 1.0000 33.000 0.8758 0.44662 0.44482 -0.1752 0.0075 1.0000 33.500 0.8788 0.45548 0.45371 -0.1783 0.0072 1.0000 34.000 0.8816 0.46401 0.46227 -0.1813 0.0069 1.0000 34.500 0.8839 0.47225 0.47054 -0.1844 0.0068 1.0000 35.000 0.8859 0.48043 0.47875 -0.1874 0.0066 1.0000 35.500 0.8876 0.48860 0.48695 -0.1904 0.0064 1.0000 36.000 0.8888 0.49637 0.49475 -0.1933 0.0063 1.0000 36.500 0.8897 0.50414 0.50255 -0.1962 0.0063 1.0000 37.000 0.8904 0.51178 0.51022 -0.1991 0.0062 1.0000 37.500 0.8906 0.51920 0.51768 -0.2019 0.0061 1.0000 38.000 0.8904 0.52651 0.52501 -0.2047 0.0061 1.0000 38.500 0.8900 0.53362 0.53216 -0.2075 0.0060 1.0000 39.000 0.8891 0.54048 0.53904 -0.2102 0.0060 1.0000 39.500 0.8879 0.54721 0.54581 -0.2128 0.0059 1.0000 40.000 0.8866 0.55408 0.55271 -0.2156 0.0059 1.0000 40.500 0.8847 0.56044 0.55911 -0.2180 0.0059 1.0000