XFOIL Version 6.94 Calculated polar for: BL BAP 05 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1633 0.05283 0.04382 -0.0417 0.9998 0.2877 -2.750 -0.1215 0.05108 0.04162 -0.0457 0.9998 0.2757 -2.500 -0.0636 0.04874 0.03901 -0.0527 0.9903 0.2699 -2.250 0.0148 0.04605 0.03591 -0.0634 0.9666 0.2647 -2.000 0.0849 0.04343 0.03282 -0.0715 0.9347 0.2606 -1.750 0.1280 0.04134 0.03047 -0.0739 0.8938 0.2590 -1.500 0.1090 0.04110 0.03044 -0.0655 0.8091 0.2585 -1.250 0.2047 0.03769 0.02632 -0.0759 0.7197 0.2620 -1.000 0.3136 0.03482 0.02232 -0.0890 0.6718 0.2792 -0.750 0.3763 0.03376 0.02087 -0.0952 0.6513 0.3014 -0.500 0.4267 0.03303 0.02009 -0.0992 0.6397 0.3376 -0.250 0.4591 0.02995 0.01921 -0.0988 0.6350 1.0002 0.000 0.5100 0.03060 0.01858 -0.1018 0.6316 1.0002 0.250 0.5549 0.03121 0.01851 -0.1049 0.6298 1.0002 0.500 0.5976 0.03187 0.01877 -0.1081 0.6285 1.0002 0.750 0.6391 0.03262 0.01925 -0.1113 0.6269 1.0002 1.000 0.6792 0.03347 0.01990 -0.1142 0.6253 1.0002 1.250 0.7163 0.03434 0.02069 -0.1168 0.6250 1.0002 1.500 0.7490 0.03516 0.02161 -0.1187 0.6277 1.0002 1.750 0.7813 0.03613 0.02269 -0.1208 0.6317 1.0002 2.000 0.8145 0.03729 0.02393 -0.1231 0.6352 1.0002 2.250 0.8435 0.03869 0.02546 -0.1249 0.6388 1.0002 2.500 0.8673 0.04040 0.02737 -0.1261 0.6432 1.0002 2.750 0.8760 0.04281 0.03012 -0.1257 0.6510 1.0002 3.000 0.8770 0.04639 0.03396 -0.1250 0.6626 1.0002 3.250 0.7612 0.05863 0.04664 -0.1138 0.6938 1.0002 3.500 0.6071 0.07594 0.06414 -0.1047 0.7559 1.0002 3.750 0.5172 0.08482 0.07315 -0.0974 0.8208 1.0002 4.500 0.3655 0.09373 0.08214 -0.0717 0.9998 1.0002 4.750 0.3789 0.09638 0.08468 -0.0725 0.9998 1.0002 5.000 0.3922 0.09907 0.08726 -0.0734 0.9998 1.0002