XFOIL Version 6.94 Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) AI 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 0.6425 0.00990 0.00255 -0.1249 0.6414 0.0485 0.500 0.6970 0.00979 0.00264 -0.1246 0.6201 0.1128 1.000 0.7514 0.00968 0.00273 -0.1244 0.6019 0.2183 2.000 0.8599 0.00847 0.00301 -0.1239 0.5666 1.0000 2.500 0.9138 0.00875 0.00315 -0.1235 0.5493 1.0000 3.000 0.9671 0.00907 0.00332 -0.1229 0.5319 1.0000 3.500 1.0202 0.00937 0.00353 -0.1224 0.5133 1.0000 5.000 1.1505 0.01202 0.00489 -0.1160 0.2854 1.0000 5.500 1.1914 0.01321 0.00569 -0.1137 0.2280 1.0000 6.000 1.2361 0.01403 0.00635 -0.1120 0.2006 1.0000 6.500 1.2628 0.01612 0.00773 -0.1076 0.0942 1.0000 7.000 1.2789 0.01872 0.00983 -0.1013 0.0033 1.0000 7.500 1.3142 0.01962 0.01080 -0.0979 0.0030 1.0000 8.000 1.3481 0.02065 0.01193 -0.0945 0.0030 1.0000 8.500 1.3801 0.02184 0.01323 -0.0910 0.0031 1.0000 9.000 1.4094 0.02327 0.01481 -0.0874 0.0033 1.0000 9.500 1.4350 0.02501 0.01672 -0.0836 0.0035 1.0000 10.000 1.4564 0.02717 0.01908 -0.0797 0.0036 1.0000 10.500 1.4782 0.02944 0.02150 -0.0763 0.0039 1.0000 11.000 1.4962 0.03215 0.02442 -0.0729 0.0043 1.0000 11.500 1.5069 0.03573 0.02822 -0.0696 0.0047 1.0000 12.500 1.5207 0.04450 0.03742 -0.0646 0.0054 1.0000 13.000 1.5182 0.05043 0.04359 -0.0630 0.0059 1.0000 13.500 1.5043 0.05819 0.05159 -0.0622 0.0063 1.0000 14.000 1.4875 0.06684 0.06047 -0.0623 0.0065 1.0000 14.500 1.4905 0.07318 0.06705 -0.0625 0.0073 1.0000 15.000 1.4712 0.08284 0.07695 -0.0637 0.0077 1.0000 15.500 1.4483 0.09313 0.08742 -0.0652 0.0081 1.0000 16.000 1.4483 0.10047 0.09499 -0.0665 0.0089 1.0000 16.500 1.4414 0.10788 0.10252 -0.0668 0.0100 1.0000 17.000 1.4701 0.10804 0.10271 -0.0619 0.0125 1.0000 18.000 1.0914 0.13564 0.13161 -0.0563 0.0075 1.0000 18.500 1.1017 0.13754 0.13350 -0.0557 0.0083 1.0000 19.000 1.1274 0.13714 0.13322 -0.0534 0.0104 1.0000 20.500 1.0753 0.15770 0.15516 -0.0596 0.0185 1.0000 21.000 1.0370 0.16987 0.16755 -0.0668 0.0183 1.0000 21.500 0.9924 0.18503 0.18290 -0.0766 0.0158 1.0000 22.000 0.9579 0.19862 0.19663 -0.0836 0.0153 1.0000 22.500 0.9008 0.22111 0.21923 -0.0943 0.0122 1.0000 23.000 0.8323 0.26061 0.25865 -0.1040 0.0222 1.0000 23.500 0.8366 0.26701 0.26507 -0.1060 0.0216 1.0000 24.000 0.8349 0.27642 0.27447 -0.1092 0.0199 1.0000 24.500 0.8395 0.28234 0.28041 -0.1112 0.0184 1.0000 25.000 0.8397 0.29101 0.28909 -0.1140 0.0164 1.0000 25.500 0.8461 0.29574 0.29385 -0.1156 0.0152 1.0000 26.000 0.8456 0.30501 0.30312 -0.1187 0.0131 1.0000 27.000 0.8511 0.31879 0.31694 -0.1234 0.0105 1.0000 27.500 0.8527 0.32684 0.32500 -0.1259 0.0096 1.0000 28.000 0.8556 0.33335 0.33153 -0.1282 0.0085 1.0000 28.500 0.8600 0.33818 0.33638 -0.1298 0.0081 1.0000 29.000 0.8593 0.34846 0.34668 -0.1329 0.0071 1.0000 29.500 0.8620 0.35415 0.35239 -0.1351 0.0066 1.0000 30.000 0.8638 0.36078 0.35905 -0.1372 0.0064 1.0000 30.500 0.8645 0.37012 0.36840 -0.1399 0.0057 1.0000 31.000 0.8661 0.37685 0.37516 -0.1422 0.0053 1.0000 31.500 0.8676 0.38275 0.38108 -0.1444 0.0051 1.0000 32.000 0.8695 0.38794 0.38630 -0.1463 0.0049 1.0000 32.500 0.8692 0.39672 0.39510 -0.1489 0.0048 1.0000 33.000 0.8696 0.40478 0.40319 -0.1513 0.0047 1.0000 33.500 0.8701 0.41183 0.41026 -0.1536 0.0044 1.0000 34.000 0.8704 0.41860 0.41706 -0.1559 0.0043 1.0000 34.500 0.8704 0.42514 0.42363 -0.1581 0.0041 1.0000 35.000 0.8702 0.43154 0.43006 -0.1604 0.0040 1.0000 35.500 0.8696 0.43778 0.43633 -0.1626 0.0039 1.0000 36.000 0.8689 0.44386 0.44244 -0.1649 0.0038 1.0000 36.500 0.8679 0.44978 0.44839 -0.1671 0.0038 1.0000 37.000 0.8666 0.45560 0.45424 -0.1694 0.0037 1.0000 37.500 0.8651 0.46129 0.45996 -0.1716 0.0037 1.0000 38.000 0.8633 0.46674 0.46545 -0.1738 0.0036 1.0000 38.500 0.8612 0.47179 0.47053 -0.1759 0.0036 1.0000