XFOIL Version 6.94 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AI 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6351 0.01177 0.00418 -0.1146 0.6259 0.0508 0.500 0.6908 0.01273 0.00522 -0.1144 0.6094 0.0685 1.000 0.7470 0.01256 0.00457 -0.1133 0.5923 0.0758 1.500 0.8013 0.01308 0.00503 -0.1129 0.5725 0.0968 2.000 0.8550 0.01279 0.00472 -0.1125 0.5539 0.1030 2.500 0.9081 0.01269 0.00457 -0.1120 0.5353 0.1124 3.000 0.9606 0.01269 0.00452 -0.1114 0.5156 0.1253 3.500 1.0128 0.01266 0.00455 -0.1109 0.4935 0.1449 4.000 1.0647 0.01271 0.00465 -0.1105 0.4702 0.1823 4.500 1.1112 0.01173 0.00479 -0.1090 0.4265 1.0000 5.000 1.1531 0.01268 0.00516 -0.1069 0.3520 1.0000 5.500 1.1949 0.01383 0.00604 -0.1049 0.2931 1.0000 6.000 1.2219 0.01633 0.00762 -0.1011 0.1484 1.0000 7.000 1.2776 0.02059 0.01111 -0.0935 0.0079 1.0000 7.500 1.3144 0.02160 0.01226 -0.0907 0.0087 1.0000 8.000 1.3479 0.02277 0.01358 -0.0874 0.0101 1.0000 8.500 1.3785 0.02420 0.01520 -0.0840 0.0115 1.0000 9.000 1.4026 0.02618 0.01742 -0.0802 0.0116 1.0000 9.500 1.4203 0.02882 0.02033 -0.0762 0.0117 1.0000 10.000 1.4316 0.03225 0.02405 -0.0725 0.0117 1.0000 10.500 1.4346 0.03678 0.02885 -0.0692 0.0116 1.0000 11.000 1.4305 0.04250 0.03482 -0.0668 0.0117 1.0000 11.500 1.4204 0.04937 0.04192 -0.0653 0.0118 1.0000 12.000 1.4091 0.05677 0.04951 -0.0645 0.0120 1.0000 12.500 1.3988 0.06423 0.05714 -0.0638 0.0122 1.0000 13.000 1.3931 0.07111 0.06414 -0.0630 0.0123 1.0000 13.500 1.3957 0.07661 0.06970 -0.0613 0.0121 1.0000