XFOIL Version 6.94 Calculated polar for: GM15 (smoothed) 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 0.5668 0.00881 0.00300 -0.1361 0.8872 0.3961 0.500 0.6239 0.00845 0.00274 -0.1356 0.8606 0.4496 1.000 0.6767 0.00803 0.00259 -0.1343 0.8250 0.5469 1.500 0.7384 0.00724 0.00243 -0.1348 0.7825 1.0000 2.000 0.7907 0.00755 0.00245 -0.1334 0.7351 1.0000 2.500 0.8412 0.00796 0.00266 -0.1318 0.6897 1.0000 3.000 0.8910 0.00842 0.00293 -0.1301 0.6481 1.0000 3.500 0.9404 0.00890 0.00328 -0.1284 0.6087 1.0000 4.000 0.9893 0.00940 0.00373 -0.1267 0.5685 1.0000 4.500 1.0363 0.00995 0.00418 -0.1246 0.5189 1.0000 5.000 1.0769 0.01083 0.00465 -0.1213 0.4235 1.0000 5.500 1.1180 0.01194 0.00542 -0.1185 0.3282 1.0000 6.000 1.1446 0.01485 0.00703 -0.1140 0.0999 1.0000 6.500 1.1736 0.01796 0.00983 -0.1092 0.0303 1.0000 7.000 1.2104 0.01988 0.01203 -0.1055 0.0256 1.0000 7.500 1.2391 0.02279 0.01509 -0.1008 0.0213 1.0000 8.000 1.2706 0.02657 0.01915 -0.0966 0.0184 1.0000 8.500 1.3104 0.03063 0.02357 -0.0936 0.0168 1.0000 9.000 1.3479 0.03668 0.03019 -0.0904 0.0164 1.0000 9.500 1.3731 0.04081 0.03479 -0.0862 0.0145 1.0000 10.000 1.3806 0.04794 0.04265 -0.0800 0.0145 1.0000 10.500 1.3542 0.05736 0.05288 -0.0707 0.0163 1.0000 11.000 1.3136 0.06545 0.06146 -0.0633 0.0175 1.0000 11.500 1.2663 0.07562 0.07203 -0.0607 0.0185 1.0000 12.000 1.2096 0.09137 0.08844 -0.0641 0.0261 1.0000 12.500 1.1612 0.10741 0.10475 -0.0740 0.0268 1.0000 13.000 1.1137 0.12896 0.12648 -0.0891 0.0280 1.0000