XFOIL Version 6.94 Calculated polar for: GOE 275 (DAIMLER VI) 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 0.5356 0.01108 0.00401 -0.0993 0.6168 0.0260 0.500 0.5822 0.01101 0.00360 -0.0972 0.5530 0.0287 1.000 0.6186 0.00325 -0.00431 -0.0930 0.4653 0.0512 1.500 0.6661 0.00310 -0.00469 -0.0912 0.4157 0.0453 2.000 0.7147 0.00303 -0.00491 -0.0898 0.3843 0.0448 2.500 0.7648 0.00301 -0.00497 -0.0887 0.3665 0.0477 3.000 0.8146 0.00305 -0.00501 -0.0876 0.3510 0.0512 3.500 0.8633 0.00264 -0.00442 -0.0869 0.3389 0.5778 5.000 1.0037 0.00317 -0.00407 -0.0826 0.1783 1.0000 5.500 1.0450 0.00375 -0.00379 -0.0805 0.1292 1.0000 6.000 1.0838 0.00453 -0.00336 -0.0780 0.0729 1.0000 7.000 1.1595 0.00628 -0.00190 -0.0725 0.0036 1.0000 7.500 1.2004 0.00688 -0.00119 -0.0701 0.0037 1.0000 8.000 1.2386 0.00761 -0.00032 -0.0674 0.0040 1.0000 8.500 1.2743 0.00837 0.00060 -0.0642 0.0046 1.0000 9.000 1.3020 0.00931 0.00172 -0.0597 0.0052 1.0000 9.500 1.3268 0.01026 0.00286 -0.0549 0.0059 1.0000 10.000 1.3459 0.01157 0.00440 -0.0496 0.0067 1.0000 10.500 1.3642 0.01296 0.00602 -0.0447 0.0076 1.0000 11.000 1.3689 0.01534 0.00867 -0.0390 0.0084 1.0000 11.500 1.3656 0.01874 0.01234 -0.0339 0.0089 1.0000 12.000 1.3606 0.02322 0.01709 -0.0300 0.0097 1.0000 12.500 1.3389 0.03090 0.02507 -0.0276 0.0101 1.0000 13.000 1.3104 0.04191 0.03639 -0.0281 0.0105 1.0000 14.000 1.2687 0.06656 0.06161 -0.0335 0.0115 1.0000 14.500 1.2486 0.07917 0.07445 -0.0370 0.0123 1.0000 15.000 1.2485 0.08751 0.08296 -0.0385 0.0137 1.0000 15.500 1.3270 0.08308 0.07867 -0.0273 0.0187 1.0000 16.000 1.2864 0.09781 0.09423 -0.0336 0.0224 1.0000 16.500 1.2026 0.11774 0.11500 -0.0480 0.0261 1.0000 17.000 1.1345 0.13760 0.13534 -0.0638 0.0265 1.0000 17.500 1.0912 0.15421 0.15220 -0.0764 0.0260 1.0000 18.000 1.0515 0.17170 0.16988 -0.0888 0.0256 1.0000 18.500 1.0098 0.19148 0.18977 -0.1026 0.0213 1.0000