XFOIL Version 6.94 Calculated polar for: GOE 13K 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 ------- -------- --------- --------- -------- ------- ------- 1.500 0.5781 0.01727 0.01322 -0.1184 0.7896 0.9812 2.000 0.7180 0.01669 0.01255 -0.1365 0.7915 1.0000 2.500 0.7849 0.01601 0.01180 -0.1387 0.7895 1.0000 3.500 0.9162 0.01219 0.00752 -0.1397 0.7242 1.0000 4.000 0.9207 0.01296 0.00814 -0.1291 0.6779 1.0000 4.500 0.8619 0.01594 0.01028 -0.1067 0.5146 1.0000 5.000 0.8350 0.01894 0.01274 -0.0922 0.4195 1.0000 5.500 0.8466 0.02069 0.01419 -0.0850 0.3614 1.0000 6.000 0.8384 0.02354 0.01624 -0.0751 0.2221 1.0000 6.500 0.8395 0.02621 0.01806 -0.0672 0.0774 1.0000 7.000 0.8718 0.02733 0.01908 -0.0641 0.0589 1.0000 7.500 0.8952 0.02903 0.02048 -0.0597 0.0055 1.0000 8.000 0.9292 0.03012 0.02158 -0.0570 0.0046 1.0000 8.500 0.9625 0.03127 0.02277 -0.0542 0.0046 1.0000 9.000 0.9953 0.03249 0.02404 -0.0515 0.0047 1.0000 9.500 1.0269 0.03381 0.02543 -0.0487 0.0050 1.0000 10.000 1.0570 0.03526 0.02696 -0.0457 0.0054 1.0000 10.500 1.0859 0.03681 0.02862 -0.0427 0.0056 1.0000 11.000 1.1117 0.03861 0.03054 -0.0395 0.0059 1.0000 11.500 1.1354 0.04061 0.03269 -0.0361 0.0060 1.0000 12.000 1.1624 0.04242 0.03460 -0.0333 0.0067 1.0000 12.500 1.1851 0.04460 0.03692 -0.0301 0.0075 1.0000 13.000 1.2030 0.04719 0.03969 -0.0267 0.0077 1.0000 13.500 1.2251 0.04954 0.04216 -0.0239 0.0086 1.0000 14.000 1.2403 0.05256 0.04534 -0.0206 0.0096 1.0000 14.500 1.2547 0.05575 0.04867 -0.0176 0.0105 1.0000 15.000 1.2653 0.05940 0.05249 -0.0146 0.0118 1.0000 15.500 1.2792 0.06288 0.05614 -0.0121 0.0132 1.0000 16.000 1.2798 0.06782 0.06126 -0.0094 0.0140 1.0000 16.500 1.2848 0.07252 0.06612 -0.0072 0.0154 1.0000 17.000 1.2821 0.07808 0.07183 -0.0050 0.0173 1.0000 17.500 1.2954 0.08209 0.07609 -0.0034 0.0196 1.0000 18.000 1.3048 0.08619 0.08029 -0.0015 0.0207 1.0000 18.500 1.3476 0.08561 0.07987 0.0027 0.0237 1.0000 19.000 1.3859 0.08785 0.08267 0.0064 0.0273 1.0000 20.500 1.0761 0.15852 0.15597 -0.0194 0.0368 1.0000 21.000 1.0253 0.17863 0.17622 -0.0321 0.0360 1.0000 21.500 0.8887 0.13314 0.13056 -0.0047 0.0280 1.0000 22.000 0.8406 0.14468 0.14228 -0.0122 0.0273 1.0000 22.500 0.9200 0.24589 0.24334 -0.0676 0.0363 1.0000 23.500 0.9382 0.25872 0.25616 -0.0747 0.0317 1.0000 24.000 0.9454 0.26552 0.26294 -0.0790 0.0280 1.0000 24.500 0.9543 0.27190 0.26931 -0.0829 0.0246 1.0000 25.000 0.9730 0.27381 0.27124 -0.0833 0.0235 1.0000 25.500 0.9739 0.28315 0.28055 -0.0902 0.0193 1.0000 26.000 0.9870 0.28653 0.28395 -0.0928 0.0177 1.0000 26.500 0.9953 0.29283 0.29025 -0.0970 0.0152 1.0000 27.000 1.0041 0.29902 0.29643 -0.1012 0.0133 1.0000 27.500 1.0163 0.30203 0.29946 -0.1037 0.0125 1.0000 28.000 1.0237 0.30945 0.30686 -0.1086 0.0108 1.0000 28.500 1.0350 0.31231 0.30974 -0.1114 0.0102 1.0000 29.000 1.0426 0.31978 0.31720 -0.1162 0.0091 1.0000 29.500 1.0524 0.32400 0.32144 -0.1197 0.0084 1.0000 30.000 1.0628 0.32641 0.32386 -0.1225 0.0080 1.0000 30.500 1.0704 0.33404 0.33148 -0.1275 0.0075 1.0000 31.000 1.0794 0.33892 0.33637 -0.1314 0.0070 1.0000 31.500 1.0882 0.34296 0.34043 -0.1351 0.0065 1.0000 32.000 1.0968 0.34612 0.34360 -0.1386 0.0062 1.0000 32.500 1.1053 0.34868 0.34619 -0.1417 0.0061 1.0000 33.000 1.1129 0.35264 0.35016 -0.1453 0.0060 1.0000 33.500 1.1205 0.35976 0.35728 -0.1506 0.0058 1.0000 34.000 1.1283 0.36406 0.36160 -0.1546 0.0056 1.0000 34.500 1.1356 0.36792 0.36548 -0.1585 0.0054 1.0000 35.000 1.1428 0.37145 0.36903 -0.1625 0.0051 1.0000 35.500 1.1494 0.37457 0.37216 -0.1665 0.0051 1.0000 36.000 1.1559 0.37747 0.37509 -0.1705 0.0050 1.0000 36.500 1.1620 0.38020 0.37783 -0.1745 0.0048 1.0000 37.000 1.1677 0.38276 0.38042 -0.1785 0.0048 1.0000 37.500 1.1731 0.38524 0.38292 -0.1825 0.0047 1.0000 38.000 1.1781 0.38723 0.38493 -0.1865 0.0046 1.0000 38.500 1.1825 0.38909 0.38682 -0.1905 0.0045 1.0000 39.000 1.1873 0.39200 0.38976 -0.1948 0.0046 1.0000 39.500 1.1911 0.39382 0.39159 -0.1988 0.0045 1.0000 40.000 1.1949 0.39620 0.39401 -0.2030 0.0045 1.0000 40.500 1.1984 0.39856 0.39639 -0.2072 0.0046 1.0000 41.000 1.2012 0.40041 0.39826 -0.2113 0.0046 1.0000