XFOIL Version 6.96 Calculated polar for: GOE 344 (PFALZ 71) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5069 0.11712 0.10972 -0.0078 1.0000 0.1137 -9.000 -0.5132 0.11446 0.10715 -0.0105 1.0000 0.1142 -8.750 -0.5180 0.11141 0.10418 -0.0127 1.0000 0.1143 -8.250 -0.4992 0.09914 0.09186 -0.0137 1.0000 0.0848 -8.000 -0.4944 0.09518 0.08793 -0.0139 1.0000 0.0823 -7.750 -0.4927 0.09132 0.08408 -0.0157 1.0000 0.0815 -7.500 -0.4901 0.08737 0.08015 -0.0176 1.0000 0.0809 -7.250 -0.4864 0.08321 0.07599 -0.0196 1.0000 0.0796 -6.750 -0.4777 0.07106 0.06356 -0.0293 1.0000 0.0724 -6.500 -0.4674 0.06684 0.05924 -0.0301 1.0000 0.0721 -6.250 -0.4562 0.06222 0.05449 -0.0316 1.0000 0.0733 -6.000 -0.4431 0.06092 0.05326 -0.0296 1.0000 0.0766 -5.750 -0.4286 0.05718 0.04935 -0.0304 1.0000 0.0779 -5.500 -0.4125 0.05270 0.04460 -0.0315 1.0000 0.0776 -5.250 -0.3949 0.04845 0.04004 -0.0323 1.0000 0.0776 -5.000 -0.3760 0.04460 0.03584 -0.0327 1.0000 0.0782 -4.750 -0.3559 0.04152 0.03239 -0.0327 1.0000 0.0811 -4.500 -0.3343 0.03812 0.02845 -0.0328 1.0000 0.0843 -4.250 -0.3116 0.03493 0.02470 -0.0325 1.0000 0.0856 -4.000 -0.2884 0.03231 0.02161 -0.0320 1.0000 0.0870 -3.750 -0.2657 0.03065 0.01979 -0.0313 1.0000 0.0891 -3.500 -0.2421 0.02911 0.01800 -0.0307 1.0000 0.0918 -3.250 -0.2177 0.02771 0.01628 -0.0300 1.0000 0.0973 -3.000 -0.1931 0.02656 0.01492 -0.0294 1.0000 0.1035 -2.750 -0.1682 0.02553 0.01372 -0.0288 1.0000 0.1098 -2.500 -0.1422 0.02440 0.01234 -0.0282 1.0000 0.1166 -2.250 -0.1163 0.02361 0.01137 -0.0276 1.0000 0.1274 -2.000 -0.0905 0.02304 0.01073 -0.0271 1.0000 0.1430 -1.750 -0.0641 0.02246 0.01016 -0.0268 1.0000 0.1610 -1.500 -0.0384 0.02198 0.00969 -0.0264 1.0000 0.1832 -1.250 -0.0132 0.02154 0.00932 -0.0260 1.0000 0.2057 -1.000 0.0115 0.02118 0.00903 -0.0254 1.0000 0.2291 -0.750 0.0357 0.02085 0.00878 -0.0248 1.0000 0.2526 -0.500 0.0595 0.02056 0.00862 -0.0242 1.0000 0.2821 -0.250 0.0831 0.02023 0.00851 -0.0236 1.0000 0.3228 0.000 0.1062 0.01963 0.00840 -0.0232 1.0000 0.4021 0.250 0.1407 0.01829 0.00838 -0.0242 1.0000 1.0000 0.500 0.1705 0.01858 0.00847 -0.0251 0.9953 1.0000 0.750 0.2256 0.01872 0.00841 -0.0309 0.9753 1.0000 1.000 0.2726 0.01873 0.00833 -0.0348 0.9530 1.0000 1.250 0.3174 0.01868 0.00822 -0.0381 0.9289 1.0000 1.500 0.3646 0.01855 0.00807 -0.0415 0.9054 1.0000 1.750 0.4073 0.01840 0.00793 -0.0439 0.8766 1.0000 2.000 0.4434 0.01830 0.00784 -0.0449 0.8391 1.0000 2.250 0.4817 0.01817 0.00769 -0.0461 0.7971 1.0000 2.500 0.5218 0.01807 0.00747 -0.0473 0.7507 1.0000 2.750 0.5567 0.01816 0.00736 -0.0475 0.7021 1.0000 3.000 0.5847 0.01847 0.00748 -0.0467 0.6545 1.0000 3.250 0.6095 0.01889 0.00770 -0.0454 0.6089 1.0000 3.500 0.6333 0.01936 0.00799 -0.0441 0.5678 1.0000 3.750 0.6567 0.01987 0.00836 -0.0428 0.5311 1.0000 4.000 0.6802 0.02042 0.00878 -0.0417 0.4990 1.0000 4.250 0.7045 0.02098 0.00926 -0.0408 0.4701 1.0000 4.500 0.7290 0.02155 0.00980 -0.0400 0.4447 1.0000 4.750 0.7536 0.02214 0.01034 -0.0393 0.4218 1.0000 5.000 0.7783 0.02273 0.01093 -0.0386 0.4004 1.0000 5.250 0.8025 0.02335 0.01158 -0.0378 0.3795 1.0000 5.750 0.8486 0.02464 0.01287 -0.0359 0.3357 1.0000 6.000 0.8702 0.02531 0.01347 -0.0348 0.3130 1.0000 6.250 0.8915 0.02597 0.01428 -0.0337 0.2891 1.0000 6.500 0.9123 0.02666 0.01499 -0.0325 0.2673 1.0000 6.750 0.9330 0.02737 0.01586 -0.0313 0.2437 1.0000 7.000 0.9526 0.02814 0.01664 -0.0299 0.2216 1.0000 7.250 0.9724 0.02903 0.01772 -0.0287 0.1977 1.0000 7.500 0.9908 0.03000 0.01866 -0.0273 0.1767 1.0000 7.750 1.0100 0.03120 0.01995 -0.0259 0.1583 1.0000 8.000 1.0285 0.03248 0.02129 -0.0246 0.1436 1.0000 8.250 1.0464 0.03381 0.02268 -0.0232 0.1310 1.0000 8.500 1.0641 0.03527 0.02414 -0.0219 0.1219 1.0000 8.750 1.0823 0.03701 0.02621 -0.0205 0.1130 1.0000 9.000 1.0984 0.03867 0.02795 -0.0191 0.1050 1.0000 9.250 1.1140 0.04053 0.03003 -0.0176 0.0977 1.0000 9.500 1.1280 0.04259 0.03227 -0.0161 0.0912 1.0000 9.750 1.1393 0.04453 0.03444 -0.0143 0.0842 1.0000 10.000 1.1495 0.04688 0.03697 -0.0126 0.0788 1.0000 10.250 1.1553 0.04944 0.03991 -0.0106 0.0734 1.0000 10.500 1.1645 0.05159 0.04209 -0.0090 0.0692 1.0000 10.750 1.1620 0.05499 0.04595 -0.0065 0.0661 1.0000 11.000 1.1543 0.05845 0.04983 -0.0041 0.0633 1.0000 11.250 1.1431 0.06169 0.05335 -0.0015 0.0613 1.0000 11.500 1.1311 0.06518 0.05705 0.0004 0.0598 1.0000 11.750 1.1171 0.06918 0.06126 0.0012 0.0588 1.0000 12.000 1.0988 0.07410 0.06639 0.0007 0.0582 1.0000 12.250 1.0628 0.08247 0.07507 -0.0035 0.0593 1.0000 12.500 1.0022 0.09868 0.09151 -0.0150 0.0638 1.0000