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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4151 0.00824 0.00268 -0.0988 0.7211 0.6232 0.500 0.4635 0.00818 0.00270 -0.0972 0.7030 0.6561 1.000 0.5125 0.00816 0.00278 -0.0957 0.6872 0.6968 1.500 0.5620 0.00819 0.00289 -0.0942 0.6724 0.7448 2.000 0.6085 0.00818 0.00302 -0.0921 0.6567 0.7973 2.500 0.6551 0.00817 0.00321 -0.0900 0.6416 0.8569 3.000 0.7168 0.00829 0.00334 -0.0910 0.6008 0.9350 3.500 0.8096 0.00875 0.00362 -0.0993 0.5576 0.9819 4.000 0.8381 0.00949 0.00391 -0.0943 0.4750 1.0000 4.500 0.8476 0.01014 0.00424 -0.0851 0.4131 1.0000 5.000 0.8517 0.01118 0.00485 -0.0752 0.3353 1.0000 5.500 0.8558 0.01271 0.00580 -0.0661 0.2347 1.0000 6.000 0.8428 0.01537 0.00758 -0.0551 0.0720 1.0000 6.500 0.8637 0.01681 0.00878 -0.0499 0.0269 1.0000 7.000 0.8969 0.01773 0.00970 -0.0468 0.0221 1.0000 7.500 0.9238 0.01905 0.01095 -0.0430 0.0037 1.0000 8.000 0.9556 0.02020 0.01214 -0.0401 0.0030 1.0000 8.500 0.9862 0.02148 0.01351 -0.0371 0.0029 1.0000 9.000 1.0147 0.02297 0.01509 -0.0342 0.0029 1.0000 9.500 1.0412 0.02467 0.01691 -0.0313 0.0029 1.0000 10.000 1.0655 0.02661 0.01897 -0.0284 0.0030 1.0000 10.500 1.0881 0.02879 0.02128 -0.0257 0.0031 1.0000 11.000 1.1084 0.03124 0.02388 -0.0231 0.0031 1.0000 11.500 1.1280 0.03391 0.02670 -0.0208 0.0033 1.0000 12.000 1.1456 0.03687 0.02981 -0.0186 0.0034 1.0000 12.500 1.1602 0.04025 0.03336 -0.0167 0.0035 1.0000 13.000 1.1720 0.04409 0.03737 -0.0149 0.0038 1.0000 13.500 1.1786 0.04861 0.04208 -0.0134 0.0040 1.0000 14.000 1.1812 0.05377 0.04742 -0.0123 0.0041 1.0000 14.500 1.1787 0.05971 0.05354 -0.0116 0.0042 1.0000 15.000 1.1749 0.06605 0.06005 -0.0113 0.0043 1.0000 15.500 1.1821 0.07132 0.06549 -0.0114 0.0045 1.0000 16.000 1.1838 0.07740 0.07178 -0.0118 0.0048 1.0000 16.500 1.1810 0.08412 0.07870 -0.0124 0.0050 1.0000 17.000 1.1755 0.09123 0.08602 -0.0131 0.0054 1.0000 17.500 1.1698 0.09840 0.09337 -0.0139 0.0056 1.0000 18.000 1.1706 0.10464 0.09976 -0.0146 0.0060 1.0000 18.500 1.1657 0.11270 0.10815 -0.0172 0.0063 1.0000 19.000 1.1498 0.12253 0.11841 -0.0204 0.0068 1.0000 19.500 1.1274 0.13404 0.13028 -0.0253 0.0072 1.0000 20.000 1.1005 0.14713 0.14370 -0.0320 0.0075 1.0000 20.500 1.0712 0.16194 0.15883 -0.0407 0.0076 1.0000 21.000 1.0364 0.17992 0.17714 -0.0522 0.0075 1.0000 23.000 0.7595 0.27364 0.27179 -0.1089 0.0134 1.0000 23.500 0.7691 0.28113 0.27930 -0.1123 0.0127 1.0000 24.000 0.7840 0.28720 0.28539 -0.1142 0.0124 1.0000 24.500 0.7834 0.29981 0.29801 -0.1202 0.0109 1.0000 25.000 0.7925 0.30716 0.30537 -0.1235 0.0102 1.0000 25.500 0.8026 0.31447 0.31271 -0.1264 0.0099 1.0000 26.000 0.8064 0.32596 0.32420 -0.1311 0.0086 1.0000 26.500 0.8142 0.33378 0.33205 -0.1345 0.0080 1.0000 27.500 0.8273 0.35244 0.35074 -0.1416 0.0072 1.0000 28.000 0.8338 0.36127 0.35958 -0.1450 0.0066 1.0000 28.500 0.8402 0.36960 0.36794 -0.1484 0.0062 1.0000 29.000 0.8465 0.37712 0.37548 -0.1516 0.0060 1.0000 29.500 0.8523 0.38581 0.38419 -0.1547 0.0058 1.0000 30.000 0.8566 0.39612 0.39452 -0.1584 0.0057 1.0000 30.500 0.8615 0.40573 0.40415 -0.1617 0.0054 1.0000 31.000 0.8662 0.41482 0.41326 -0.1650 0.0050 1.0000 31.500 0.8705 0.42355 0.42201 -0.1682 0.0049 1.0000 32.000 0.8745 0.43207 0.43056 -0.1713 0.0047 1.0000 32.500 0.8781 0.44041 0.43892 -0.1745 0.0046 1.0000 33.000 0.8813 0.44874 0.44727 -0.1776 0.0045 1.0000 33.500 0.8842 0.45669 0.45525 -0.1807 0.0044 1.0000 34.000 0.8868 0.46440 0.46298 -0.1836 0.0043 1.0000 34.500 0.8892 0.47234 0.47095 -0.1864 0.0042 1.0000 35.500 0.8922 0.48961 0.48825 -0.1924 0.0042 1.0000 36.000 0.8933 0.49766 0.49633 -0.1954 0.0042 1.0000 36.500 0.8940 0.50569 0.50438 -0.1983 0.0042 1.0000 37.000 0.8945 0.51340 0.51212 -0.2012 0.0042 1.0000 37.500 0.8946 0.52122 0.51997 -0.2040 0.0042 1.0000 38.000 0.8944 0.52875 0.52751 -0.2068 0.0042 1.0000 38.500 0.8938 0.53608 0.53487 -0.2096 0.0042 1.0000 39.000 0.8928 0.54311 0.54193 -0.2123 0.0042 1.0000 39.500 0.8916 0.55031 0.54916 -0.2150 0.0042 1.0000